JPAD test within Jupyter running a BeakerX Java kernel

— Agostino De Marco, University of Naples Federico II

JPAD stands for Java Program toolchain for Aircraft Designers. JPAD is a Java software library containing classes and utility functions that can be used to build software systems. Typically, these are calculation programs providing aerodynamic and performance predictions for given aircraft designs.

JPAD is open source and its public repository is on GitHub.

This Jupyter notebook uses the BeakerX Java kernel. The purpose is demonstrating:

  • the use of Java with Jupyter
  • the use of JPAD and its companion external native libraries in the context of a notebook

Running this notebook

Let us print the current directory content. We are Java users, so let start using Java in our first code cell to this purpose:

In [1]:
import java.nio.file.*;
Files.list(Paths.get("."))
    .forEach(System.out::println);
.\.ipynb_checkpoints
.\;
.\beakerx-jpad.bat
.\images
.\jar
.\lib
.\Test_JPAD_1.ipynb
Out[1]:
null

This notebook is named Test_JPAD_1.ipynb. The jar subdirectory contains the two Jar files

  • JPADConfigs_31032018.jar
  • JPADCore_v2_31032018.jar

where JPAD is bundled, and all the Jar's that JPAD depends upon.

In addition, the The lib subdirectory contains all the native libraries (Win64) needed for JPAD to work correctly.

The BeakerX kernel for this notebook is launched on Windows with the following beakerx-jpad.bat file:

setlocal
set PATH=%PATH%;.\lib;.\jar;
set JUPYTER_RUNTIME_DIR=%JUPYTER_RUNTIME_DIR%;.\lib
set JUPYTER_EXEC="beakerx"

%JUPYTER_EXEC%

It adds lib and jar directories to the PATH environment variables as well as to the JUPYTER_RUNTIME_DIR. Then, it runs Jupyter with the beakerx command. Once Jupyter with the BeakerX kernel is set up and running, the notebook file can be opened and executed.

Preliminaries

Classpath extras

The following cell uses BeakerX magic command %classpath that directs the Java kernel to include all the Jar files located in the path ./jar. The command %classpath alone prints out all the included Jars.

In [2]:
%classpath add jar .\jar\*
%classpath
Added jars: [xstream-1.4.7.jar, jarh4obj.jar, jxls-core-1.0.5.jar, jarh5obj.jar, flanagan.jar, dom4j-1.6.1.jar, log4j-1.2.13.jar, xmlbeans-2.6.0.jar, JPADConfigs_31032018.jar, processing-core.jar, freebuilder-1.10.5.jar, commons-codec-1.5.jar, jfreesvg-3.0.jar, MOEAFramework-2.12.jar, jdom-2.0.5.jar, unit-api-0.6.1.jar, commons-lang3-3.7.jar, jarhdf-2.10.1.jar, vecmath.jar, trove-3.1a1.jar, commons-logging-1.1.jar, slf4j-api-1.7.5.jar, jfreechart-1.5.0.jar, jarhdfobj.jar, jxls-reader-1.0.5.jar, orsonpdf-1.7.jar, fxgraphics2d-1.3.jar, commons-logging-1.2.jar, jfreesvg-3.3.jar, commons-math3-3.6.1.jar, log4j-core-2.0.2.jar, commons-jexl-2.1.1.jar, reflectutils-0.9.16.jar, jarhdf5-2.10.1.jar, jfreechart-nofx-2.0-pre1.jar, commons-collections4-4.0.jar, javaslang-2.0.4.jar, gtmat.jar, orsoncharts-1.5.jar, poi-3.10.1-20140818.jar, junit-4.11.jar, JPADCore_v2_31032018.jar, tigl-2.2.1.jar, stax-api-1.0.1.jar, jscience.jar, log4j-api-2.0.2.jar, guava-16.0.1.jar, poi-ooxml-3.10.1-20140818.jar, icu4j-59_1.jar]
C:\Users\agodemar\AppData\Local\Temp\beaker8127997811507948280\outDir
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\xstream-1.4.7.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\jarh4obj.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\jxls-core-1.0.5.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\jarh5obj.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\flanagan.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\dom4j-1.6.1.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\log4j-1.2.13.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\xmlbeans-2.6.0.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\JPADConfigs_31032018.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\processing-core.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\freebuilder-1.10.5.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\commons-codec-1.5.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\jfreesvg-3.0.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\MOEAFramework-2.12.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\jdom-2.0.5.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\unit-api-0.6.1.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\commons-lang3-3.7.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\jarhdf-2.10.1.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\vecmath.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\trove-3.1a1.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\commons-logging-1.1.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\slf4j-api-1.7.5.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\jfreechart-1.5.0.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\jarhdfobj.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\jxls-reader-1.0.5.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\orsonpdf-1.7.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\fxgraphics2d-1.3.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\commons-logging-1.2.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\jfreesvg-3.3.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\commons-math3-3.6.1.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\log4j-core-2.0.2.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\commons-jexl-2.1.1.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\reflectutils-0.9.16.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\jarhdf5-2.10.1.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\jfreechart-nofx-2.0-pre1.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\commons-collections4-4.0.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\javaslang-2.0.4.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\gtmat.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\orsoncharts-1.5.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\poi-3.10.1-20140818.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\junit-4.11.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\JPADCore_v2_31032018.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\tigl-2.2.1.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\stax-api-1.0.1.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\jscience.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\log4j-api-2.0.2.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\guava-16.0.1.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\poi-ooxml-3.10.1-20140818.jar
C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\jar\icu4j-59_1.jar

Check the native libs

The native libs stored in the ./lib directory are listed by the following code cell.

In [3]:
import java.nio.file.*;
Files.list(Paths.get("./lib")) // a stream of paths
    .map(path -> path.toString().toLowerCase())
    .filter(name -> name.matches("([^\\s]+(\\.(?i)(lib|dll))$)")) // use regex
    .forEach(System.out::println);
.\lib\jhdf.dll
.\lib\jhdf.lib
.\lib\jhdf5.dll
.\lib\jhdf5.lib
.\lib\libhdf.lib
.\lib\libhdf5.lib
.\lib\libjpeg.lib
.\lib\libmfhdf.lib
.\lib\libszip.lib
.\lib\libxdr.lib
.\lib\libzlib.lib
.\lib\msvcp100.dll
.\lib\msvcr100.dll
.\lib\tbb.dll
.\lib\tbbmalloc.dll
.\lib\tigl.dll
.\lib\tigl.lib
.\lib\tixi.dll
.\lib\vcomp100.dll
Out[3]:
null

Calling JPAD functions

At this point we can start using the JPAD API functions.

Global scope imports

The following are BeakerX magics, a bunch of %import commands that make a set of Java packages globally visible by all the subsequent code cells.

In [4]:
%import java.io.File
%import java.io.IOException
%import java.io.OutputStream
%import java.io.PrintStream

%import java.nio.file.Paths
%import java.nio.file.Files

%import java.util.ArrayList
%import java.util.List

%import javax.measure.quantity.*
%import javax.measure.unit.SI

%import org.jscience.physics.amount.Amount

%import org.apache.poi.openxml4j.exceptions.InvalidFormatException

%import ncsa.hdf.hdf5lib.exceptions.HDF5LibraryException

%import configuration.*
%import configuration.enumerations.*

%import aircraft.*
%import aircraft.components.*

%import aircraft.components.FuelTank

%import aircraft.components.fuselage.*
%import aircraft.components.liftingSurface.*
%import aircraft.components.liftingSurface.creator.*
%import aircraft.components.nacelles.*
%import aircraft.components.powerplant.*

// TODO: analyses
// TODO: cad

%import calculators.*
%import calculators.aerodynamics.*
%import calculators.balance.*
%import calculators.costs.*
%import calculators.geometry.*
%import calculators.performance.*
%import calculators.stability.*
%import calculators.weights.*

%import database.*
%import database.databasefunctions.*
%import database.databasefunctions.aerodynamics.*
%import database.databasefunctions.aerodynamics.fusDes.*
%import database.databasefunctions.aerodynamics.vedsc.*
%import database.databasefunctions.engine.*

%import standaloneutils.*
%import standaloneutils.atmosphere.*
%import standaloneutils.cpacs.*
%import standaloneutils.customdata.*
%import standaloneutils.database.*
%import standaloneutils.jsbsim.*
%import standaloneutils.launchers.*
%import standaloneutils.mathtools.*
%import standaloneutils.aerotools.*

%import writers.*

Setup database files and create an Aircraft object

We will read the input file ../in/aircraft_IRON_NEW.xml that defines a specific aircraft design named IRON. The following image is a top view of this airplane.

To do so we create a package named test.jpad that wraps a test class named JPADTest. Objects of this class incorporate the paths to all the files necessary for JPAD to work correctly.

In [5]:
package test.jpad;

public class JPADTest {
    
    public String pathToXML;
    public String aircraftFileName;
    
    public String dirAirfoil;
    public String dirFuselages;
    public String dirLiftingSurfaces;
    public String dirEngines;
    public String dirNacelles;
    public String dirLandingGears;
    public String dirCabinConfiguration;
    
    public String databaseFolderPath;
    public String inputFolderPath;
    public String outputFolderPath;

    public AerodynamicDatabaseReader aeroDatabaseReader;
    public HighLiftDatabaseReader highLiftDatabaseReader;
    public FusDesDatabaseReader fusDesDatabaseReader;
    public VeDSCDatabaseReader veDSCDatabaseReader;

    public JPADTest(String fileName) {
        
        aircraftFileName = fileName;
        
        System.out.println("--------------------------");
        System.out.println("Initialize JPADTest");
        System.out.println("--------------------------");
        
        MyConfiguration.setDir(
            FoldersEnum.DATABASE_DIR,
            Paths.get("../data").toString()
        );
        MyConfiguration.setDir(
            FoldersEnum.INPUT_DIR,
            Paths.get("../in").toString()
        );

        MyConfiguration.setDir(
            FoldersEnum.OUTPUT_DIR,
            Paths.get("../out").toString()
        );

        String aerodynamicDatabaseFileName = "Aerodynamic_Database_Ultimate.h5";
        String highLiftDatabaseFileName = "HighLiftDatabase.h5";
        String fusDesDatabaseFilename = "FusDes_database.h5";
        String vedscDatabaseFilename = "VeDSC_database.h5";

        databaseFolderPath = MyConfiguration.getDir(FoldersEnum.DATABASE_DIR);
        inputFolderPath = MyConfiguration.getDir(FoldersEnum.INPUT_DIR);
        outputFolderPath = MyConfiguration.getDir(FoldersEnum.OUTPUT_DIR);

        System.out.println("Database dir: " + databaseFolderPath);
        System.out.println("Input dir: " + inputFolderPath);
        System.out.println("Output dir: " + outputFolderPath);

        aeroDatabaseReader = DatabaseManager.initializeAeroDatabase(
            new AerodynamicDatabaseReader(
                databaseFolderPath,
                aerodynamicDatabaseFileName
                ),
            databaseFolderPath
            );

        highLiftDatabaseReader = DatabaseManager.initializeHighLiftDatabase(
            new HighLiftDatabaseReader(
                databaseFolderPath,
                highLiftDatabaseFileName),
            databaseFolderPath
            );

        fusDesDatabaseReader = DatabaseManager.initializeFusDes(
            new FusDesDatabaseReader(
                databaseFolderPath,
                fusDesDatabaseFilename),
            databaseFolderPath
            );

        veDSCDatabaseReader = DatabaseManager.initializeVeDSC(
            new VeDSCDatabaseReader(
                databaseFolderPath,
                vedscDatabaseFilename),
            databaseFolderPath
            );

        pathToXML = inputFolderPath + "/" + aircraftFileName;
        dirAirfoil = inputFolderPath + "/lifting_surfaces/airfoils";
        dirFuselages = inputFolderPath + "/fuselages";
        dirLiftingSurfaces = inputFolderPath + "/lifting_surfaces";
        dirEngines = inputFolderPath + "/engines";
        dirNacelles = inputFolderPath + "/nacelles";
        dirLandingGears = inputFolderPath + "/landing_gears";
        dirCabinConfiguration = inputFolderPath + "/cabin_configurations";
        // atmosphere = AtmosphereCalc.getAtmosphere(1000.);

        System.out.println("--------------------------");
        System.out.println("Initialization done");
        System.out.println("--------------------------");
        
    }
}
Out[5]:
test.jpad.JPADTest

For the sake of simplicity, the class JPADTest has public member variables. Some of them are of types provided by the JPAD API. The class constructor JPADTest() defines the paths of all auxiliary input files and directories and takes as an input variable the name of the aircraft definition file (a file in XML format).

The following code cell defines an object test of type JPADTest, that incorporates all the necessary definitions to read the IRON aircraft design. The object test is initialized by passing the main aircraft definition file stored ../in/aircraft_IRON_NEW.xml

Successively, an object aircraft of type Aircraft is created and printed using the Aircraft.toString() function.

In [6]:
package test.jpad;

JPADTest test = new JPADTest("aircraft_IRON_NEW.xml");

try {
    
    System.out.println("--------------------------");
    System.out.println("Aircraft import");
    System.out.println("--------------------------");
    
    Aircraft theAircraft = Aircraft.importFromXML(
        test.pathToXML,
        test.dirLiftingSurfaces,
        test.dirFuselages,
        test.dirEngines,
        test.dirNacelles,
        test.dirLandingGears,
        test.dirCabinConfiguration,
        test.dirAirfoil,
        test.aeroDatabaseReader,
        test.highLiftDatabaseReader,
        test.fusDesDatabaseReader,
        test.veDSCDatabaseReader
        );

    // print out the object
    System.out.println(theAircraft.toString());
    
} catch (Throwable t) {
    t.printStackTrace();
    throw t;
}
--------------------------
Initialize JPADTest
--------------------------
Database dir: ..\data
Input dir: ..\in
Output dir: ..\out
De-serializing file: C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\data\serializedDatabase\interpolaterAerodynamicDatabase.xml ...
database.databasefunctions.aerodynamics.AerodynamicDatabaseReader de-serialization complete
De-serializing file: C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\data\serializedDatabase\interpolaterHighLiftDatabase.xml ...
database.databasefunctions.aerodynamics.HighLiftDatabaseReader de-serialization complete
De-serializing file: C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\data\serializedDatabase\interpolaterFusDesDatabase.xml ...
database.databasefunctions.aerodynamics.fusDes.FusDesDatabaseReader de-serialization complete
De-serializing file: C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\data\serializedDatabase\interpolaterVeDSCDatabase.xml ...
database.databasefunctions.aerodynamics.vedsc.VeDSCDatabaseReader de-serialization complete
--------------------------
Initialization done
--------------------------
--------------------------
Aircraft import
--------------------------
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\aircraft_IRON_NEW.xml found.
Parsing ...
File ..\in/aircraft_IRON_NEW.xml parsed.
Reading aircraft data from file ...
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\fuselages\fuselage_IRON.xml found.
Parsing ...
File ..\in/fuselages\fuselage_IRON.xml parsed.
Reading fuselage data ...
Spoilers found: 0
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\cabin_configurations\cabin_configuration_IRON.xml found.
Parsing ...
File ..\in/cabin_configurations\cabin_configuration_IRON.xml parsed.
Reading configuration data ...
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\lifting_surfaces\wing_IRON_NEW_v2.xml found.
Parsing ...
File ..\in/lifting_surfaces\wing_IRON_NEW_v2.xml parsed.
Reading lifting surface data ...
Panels found: 2
[0]
Panel id: IRON - Inner panel
Reading lifting surface panel data from XML doc ...
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\lifting_surfaces\airfoils\ROOT_IRON_NEW.xml found.
Parsing ...
File ..\in/lifting_surfaces/airfoils\ROOT_IRON_NEW.xml parsed.
Reading airfoil data ...
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\lifting_surfaces\airfoils\ROOT_IRON_NEW.xml found.
Parsing ...
File ..\in/lifting_surfaces/airfoils\ROOT_IRON_NEW.xml parsed.
Reading airfoil data ...
[1]
Panel id: IRON - Outer panel
Panel linked_to: **IRON - Inner panel**
Reading LINKED lifting surface panel data from XML doc ...
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\lifting_surfaces\airfoils\TIP_IRON_NEW.xml found.
Parsing ...
File ..\in/lifting_surfaces/airfoils\TIP_IRON_NEW.xml parsed.
Reading airfoil data ...
Symmetric flaps found: 2
[0]
Flap id: Inner flap
Reading symmetric flap data from XML doc ...
[1]
Flap id: Outer flap
Reading symmetric flap data from XML doc ...
Slats found: 0
Asymmetric flaps found: 2
[0]
Slat id: Left aileron
Reading asymmetric flap data from XML doc ...
[1]
Slat id: Right aileron
Reading asymmetric flap data from XML doc ...
Spoilers found: 0
[LiftingSurfaceCreator] Calculating derived geometry parameters of lifting surface ...
[LiftingSurfaceCreator] Lifting surface span ...
[LiftingSurfaceCreator] calculate variables at breakpoints ...
y Break-Points ->
[0.0 m, 5.151175326550149 m, 17.17058442183383 m]
xLE Break-Points ->
[0.0 m, 0.90829119243052858 m, 3.0276373081017618 m]
zLE Break-Points ->
[0.0 m, 0.49600176929215889 m, 1.653339230973863 m]
Chords Break-Points ->
[4.2527999999999988 m, 3.3119999999999994 m, 1.584 m]
Twists Break-Points ->
[0.0 deg, 0.0 deg, -2.0 deg]
[LiftingSurfaceCreator] Map _panels to spanwise discretized Ys ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized chords ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized Xle, Yle, twist ...
[LiftingSurfaceCreator] Map Ys to spanwise discretized variables ...
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\lifting_surfaces\htail_IRON_NEW.xml found.
Parsing ...
File ..\in/lifting_surfaces\htail_IRON_NEW.xml parsed.
Reading lifting surface data ...
Panels found: 1
[0]
Panel id: Horizontal tail panel
Reading lifting surface panel data from XML doc ...
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\lifting_surfaces\airfoils\naca0014.xml found.
Parsing ...
File ..\in/lifting_surfaces/airfoils\naca0014.xml parsed.
Reading airfoil data ...
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\lifting_surfaces\airfoils\naca0014.xml found.
Parsing ...
File ..\in/lifting_surfaces/airfoils\naca0014.xml parsed.
Reading airfoil data ...
Symmetric flaps found: 1
[0]
Flap id: Elevator
Reading symmetric flap data from XML doc ...
[LiftingSurfaceCreator] Calculating derived geometry parameters of lifting surface ...
[LiftingSurfaceCreator] Lifting surface span ...
[LiftingSurfaceCreator] calculate variables at breakpoints ...
y Break-Points ->
[0.0 m, 6.278517870878943 m]
xLE Break-Points ->
[0.0 m, 1.1070720994962233 m]
zLE Break-Points ->
[0.0 m, 1.6823237931663839 m]
Chords Break-Points ->
[3.6399999999999997 m, 2.2719999999999994 m]
Twists Break-Points ->
[0.0 deg, 0.0 deg]
[LiftingSurfaceCreator] Map _panels to spanwise discretized Ys ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized chords ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized Xle, Yle, twist ...
[LiftingSurfaceCreator] Map Ys to spanwise discretized variables ...
[LiftingSurfaceCreator] Calculating derived geometry parameters of lifting surface ...
[LiftingSurfaceCreator] Lifting surface span ...
[LiftingSurfaceCreator] calculate variables at breakpoints ...
y Break-Points ->
[0.0 m, 6.278517870878943 m]
xLE Break-Points ->
[0.0 m, 1.1070720994962233 m]
zLE Break-Points ->
[0.0 m, 1.6823237931663839 m]
Chords Break-Points ->
[3.6399999999999997 m, 2.2719999999999994 m]
Twists Break-Points ->
[0.0 deg, 0.0 deg]
[LiftingSurfaceCreator] Map _panels to spanwise discretized Ys ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized chords ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized Xle, Yle, twist ...
[LiftingSurfaceCreator] Map Ys to spanwise discretized variables ...
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\lifting_surfaces\vtail_IRON.xml found.
Parsing ...
File ..\in/lifting_surfaces\vtail_IRON.xml parsed.
Reading lifting surface data ...
Panels found: 1
[0]
Panel id: Vertical tail panel
Reading lifting surface panel data from XML doc ...
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\lifting_surfaces\airfoils\naca0012.xml found.
Parsing ...
File ..\in/lifting_surfaces/airfoils\naca0012.xml parsed.
Reading airfoil data ...
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\lifting_surfaces\airfoils\naca0012.xml found.
Parsing ...
File ..\in/lifting_surfaces/airfoils\naca0012.xml parsed.
Reading airfoil data ...
Symmetric flaps found: 1
[0]
Flap id: Rudder
Reading symmetric flap data from XML doc ...
[LiftingSurfaceCreator] Calculating derived geometry parameters of lifting surface ...
[LiftingSurfaceCreator] Lifting surface span ...
[LiftingSurfaceCreator] calculate variables at breakpoints ...
y Break-Points ->
[0.0 m, 5.779999999999999 m]
xLE Break-Points ->
[0.0 m, 5.7799999999999958 m]
zLE Break-Points ->
[0.0 m, 0.0 m]
Chords Break-Points ->
[5.16 m, 3.3099999999999996 m]
Twists Break-Points ->
[0.0 deg, 0.0 deg]
[LiftingSurfaceCreator] Map _panels to spanwise discretized Ys ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized chords ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized Xle, Yle, twist ...
[LiftingSurfaceCreator] Map Ys to spanwise discretized variables ...
[LiftingSurfaceCreator] Calculating derived geometry parameters of lifting surface ...
[LiftingSurfaceCreator] Lifting surface span ...
[LiftingSurfaceCreator] calculate variables at breakpoints ...
y Break-Points ->
[0.0 m, 5.779999999999999 m]
xLE Break-Points ->
[0.0 m, 5.7799999999999958 m]
zLE Break-Points ->
[0.0 m, 0.0 m]
Chords Break-Points ->
[5.16 m, 3.3099999999999996 m]
Twists Break-Points ->
[0.0 deg, 0.0 deg]
[LiftingSurfaceCreator] Map _panels to spanwise discretized Ys ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized chords ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized Xle, Yle, twist ...
[LiftingSurfaceCreator] Map Ys to spanwise discretized variables ...
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\lifting_surfaces\canard_IRON_v2.xml found.
Parsing ...
File ..\in/lifting_surfaces\canard_IRON_v2.xml parsed.
Reading lifting surface data ...
Panels found: 1
[0]
Panel id: Canard panel
Reading lifting surface panel data from XML doc ...
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\lifting_surfaces\airfoils\CANARD_IRON.xml found.
Parsing ...
File ..\in/lifting_surfaces/airfoils\CANARD_IRON.xml parsed.
Reading airfoil data ...
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\lifting_surfaces\airfoils\CANARD_IRON.xml found.
Parsing ...
File ..\in/lifting_surfaces/airfoils\CANARD_IRON.xml parsed.
Reading airfoil data ...
Symmetric flaps found: 1
[0]
Flap id: Control Surface
Reading symmetric flap data from XML doc ...
[LiftingSurfaceCreator] Calculating derived geometry parameters of lifting surface ...
[LiftingSurfaceCreator] Lifting surface span ...
[LiftingSurfaceCreator] calculate variables at breakpoints ...
y Break-Points ->
[0.0 m, 3.749999999999999 m]
xLE Break-Points ->
[0.0 m, 0.6612261776567433 m]
zLE Break-Points ->
[0.0 m, 0.0 m]
Chords Break-Points ->
[1.9032499999999999 m, 1.242 m]
Twists Break-Points ->
[0.0 deg, 0.0 deg]
[LiftingSurfaceCreator] Map _panels to spanwise discretized Ys ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized chords ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized Xle, Yle, twist ...
[LiftingSurfaceCreator] Map Ys to spanwise discretized variables ...
[LiftingSurfaceCreator] Calculating derived geometry parameters of lifting surface ...
[LiftingSurfaceCreator] Lifting surface span ...
[LiftingSurfaceCreator] calculate variables at breakpoints ...
y Break-Points ->
[0.0 m, 3.749999999999999 m]
xLE Break-Points ->
[0.0 m, 0.6612261776567433 m]
zLE Break-Points ->
[0.0 m, 0.0 m]
Chords Break-Points ->
[1.9032499999999999 m, 1.242 m]
Twists Break-Points ->
[0.0 deg, 0.0 deg]
[LiftingSurfaceCreator] Map _panels to spanwise discretized Ys ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized chords ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized Xle, Yle, twist ...
[LiftingSurfaceCreator] Map Ys to spanwise discretized variables ...
Engines found: 2
[0]
Engine file: engine_IRON.xml
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\engines\engine_IRON.xml found.
Parsing ...
File ..\in/engines\engine_IRON.xml parsed.
Reading systems data ...
[1]
Engine file: engine_IRON.xml
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\engines\engine_IRON.xml found.
Parsing ...
File ..\in/engines\engine_IRON.xml parsed.
Reading systems data ...
De-serializing file: C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\data\serializedDatabase\Normalized_TurboProp_100%Cruise_ISA0.xml ...
database.databasefunctions.engine.TurbopropEngineDatabaseReader de-serialization complete
Nacelles found: 2
[0]
Nacelle file: nacelle_IRON.xml
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\nacelles\nacelle_IRON.xml found.
Parsing ...
File ..\in/nacelles\nacelle_IRON.xml parsed.
Reading systems data ...
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\engines\engine_IRON.xml found.
Parsing ...
File ..\in/engines\engine_IRON.xml parsed.
Reading systems data ...
[Nacelle] Nacelle length bigger than engine length 
	 CHECK PASSED --> proceding ...
[Nacelle] calculating outlines ...
[1]
Nacelle file: nacelle_IRON.xml
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\nacelles\nacelle_IRON.xml found.
Parsing ...
File ..\in/nacelles\nacelle_IRON.xml parsed.
Reading systems data ...
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\engines\engine_IRON.xml found.
Parsing ...
File ..\in/engines\engine_IRON.xml parsed.
Reading systems data ...
[Nacelle] Nacelle length bigger than engine length 
	 CHECK PASSED --> proceding ...
[Nacelle] calculating outlines ...
File C:\Users\agodemar\Dropbox\Jupyter_2\beakerx\jpad\test2\..\in\landing_gears\landing_gear_IRON.xml found.
Parsing ...
File ..\in/landing_gears\landing_gear_IRON.xml parsed.
Reading landing gears data ...
[LiftingSurfaceCreator] Calculating derived geometry parameters of lifting surface ...
[LiftingSurfaceCreator] Lifting surface span ...
[LiftingSurfaceCreator] calculate variables at breakpoints ...
y Break-Points ->
[0.0 m, 3.9580233645174125 m, 15.977432459801094 m]
xLE Break-Points ->
[0.0 m, 0.69790630943891518 m, 2.8172524251101483 m]
zLE Break-Points ->
[0.0 m, 0.38111430251300099 m, 1.538451764194705 m]
Chords Break-Points ->
[4.034885195179683 m, 3.3119999999999994 m, 1.584 m]
Twists Break-Points ->
[0.0 deg, 0.0 deg, -2.0 deg]
[LiftingSurfaceCreator] Map _panels to spanwise discretized Ys ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized chords ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized Xle, Yle, twist ...
[LiftingSurfaceCreator] Map Ys to spanwise discretized variables ...
[LiftingSurfaceCreator] Calculating derived geometry parameters of lifting surface ...
[LiftingSurfaceCreator] Lifting surface span ...
[LiftingSurfaceCreator] calculate variables at breakpoints ...
y Break-Points ->
[0.0 m, 3.9580233645174125 m, 15.977432459801094 m]
xLE Break-Points ->
[0.0 m, 0.69790630943891518 m, 2.8172524251101483 m]
zLE Break-Points ->
[0.0 m, 0.38111430251300099 m, 1.538451764194705 m]
Chords Break-Points ->
[4.034885195179683 m, 3.3119999999999994 m, 1.584 m]
Twists Break-Points ->
[0.0 deg, 0.0 deg, -2.0 deg]
[LiftingSurfaceCreator] Map _panels to spanwise discretized Ys ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized chords ...
[LiftingSurfaceCreator] Map _panels to spanwise discretized Xle, Yle, twist ...
[LiftingSurfaceCreator] Map Ys to spanwise discretized variables ...
	-------------------------------------
	The Aircraft
	-------------------------------------
	Id: 'IRON_NEW'
	Type: 'TURBOPROP'
	-------------------------------------
	Fuselage
	-------------------------------------
	ID: 'IRON Fuselage'
	Pressurized: 'true'
	Number of decks: 1
	Roughness: 0.00000405 m
	...............................................................................................................
	Length: 38.03999999999999 m
	Nose length: 4.218635999999998 m
	Cabin length: 22.405559999999994 m
	Tail length: 11.415803999999998 m
	...............................................................................................................
	Nose length ratio: 0.1109
	Cabin length ratio: 0.589
	Tail length ratio: 0.30010000000000003
	...............................................................................................................
	Cabin width: 3.5099999999999998 m
	Cabin height: 3.564 m
	...............................................................................................................
	Nose fineness ratio: 1.192750613185926
	Cabin fineness ratio: 6.334807134053295
	Tail fineness ratio: 3.2276326331568663
	Fuselage fineness ratio: 10.755190380396089
	...............................................................................................................
	Height from ground: 1.5499999999999998 m
	...............................................................................................................
	Discretization
	Outline XY Left Top View - X (m): [0.0, 0.03450695425271988, 0.23233254253864288, 0.6510241031646729, 1.261968731880188, 1.982542634010315, 2.7082605361938477, 3.3449244499206543, 3.8407740592956543, 4.2186360359191895, 10.749680519104004, 18.21820068359375, 26.624195098876953, 27.626909255981445, 29.114490509033203, 30.974411010742188, 32.98931884765625, 34.89727020263672, 36.452125549316406, 37.48383712768555, 37.958763122558594, 38.040000915527344]
	Outline XY Left Top View - Y (m): [-0.0, -0.1571948081254959, -0.36347395181655884, -0.6283332705497742, -0.9302401542663574, -1.2300069332122803, -1.4841667413711548, -1.6583471298217773, -1.7406446933746338, -1.7549999952316284, -1.7549999952316284, -1.7549999952316284, -1.7549999952316284, -1.7406448125839233, -1.6583473682403564, -1.4841663837432861, -1.2300071716308594, -0.9302399158477783, -0.6283332705497742, -0.36347389221191406, -0.15719476342201233, -0.0]
	Outline XY Right Top View - X (m): [0.0, 0.03450695425271988, 0.23233254253864288, 0.6510241031646729, 1.261968731880188, 1.982542634010315, 2.7082605361938477, 3.3449244499206543, 3.8407740592956543, 4.2186360359191895, 10.749680519104004, 18.21820068359375, 26.624195098876953, 27.626909255981445, 29.114490509033203, 30.974411010742188, 32.98931884765625, 34.89727020263672, 36.452125549316406, 37.48383712768555, 37.958763122558594, 38.040000915527344]
	Outline XY Right Top View - Y (m): [0.0, 0.1571948081254959, 0.36347395181655884, 0.6283332705497742, 0.9302401542663574, 1.2300069332122803, 1.4841667413711548, 1.6583471298217773, 1.7406446933746338, 1.7549999952316284, 1.7549999952316284, 1.7549999952316284, 1.7549999952316284, 1.7406448125839233, 1.6583473682403564, 1.4841663837432861, 1.2300071716308594, 0.9302399158477783, 0.6283332705497742, 0.36347389221191406, 0.15719476342201233, 0.0]
	Outline XZ Upper Side View - X (m): [0.0, 0.03922219201922417, 0.2623385787010193, 0.7291469573974609, 1.399139165878296, 2.1700806617736816, 2.9165878295898438, 3.5287113189697266, 3.9505105018615723, 4.2186360359191895, 10.749680519104004, 18.21820068359375, 26.624195098876953, 27.844675064086914, 29.51898956298828, 31.462987899780273, 33.44847106933594, 35.24371337890625, 36.65413284301758, 37.562870025634766, 37.97136688232422, 38.040000915527344]
	Outline XZ Upper Side View - Z (m): [-0.8410000205039978, -0.6742891073226929, -0.4120290279388428, -0.031432028859853745, 0.4327201545238495, 0.9120644927024841, 1.3286420106887817, 1.6188870668411255, 1.757612943649292, 1.781999945640564, 1.7819998264312744, 1.781999945640564, 1.781999945640564, 1.781635046005249, 1.776628017425537, 1.7571684122085571, 1.7109954357147217, 1.6268959045410156, 1.4982138872146606, 1.3263511657714844, 1.1242704391479492, 0.9200000166893005]
	Outline XZ Lower Side View - X (m): [0.0, 0.02507648430764675, 0.17232045531272888, 0.4947783052921295, 0.9876276850700378, 1.6074670553207397, 2.291604995727539, 2.9773502349853516, 3.6213011741638184, 4.2186360359191895, 10.749680519104004, 18.21820068359375, 26.624195098876953, 27.564882278442383, 28.991596221923828, 30.79401206970215, 32.77988052368164, 34.705074310302734, 36.31870651245117, 37.42292022705078, 37.9476203918457, 38.040000915527344]
	Outline XZ Lower Side View - Z (m): [-0.8410000205039978, -0.974240243434906, -1.1178785562515259, -1.2708392143249512, -1.4234421253204346, -1.5617018938064575, -1.6716357469558716, -1.7435624599456787, -1.7764064073562622, -1.781999945640564, -1.7819998264312744, -1.781999945640564, -1.781999945640564, -1.7601486444473267, -1.6363534927368164, -1.3772556781768799, -1.0020294189453125, -0.5598637461662292, -0.10965093225240707, 0.2981375455856323, 0.6373735070228577, 0.9200000166893005]
	Outline YZ Upper Section View - Y (m): [-1.7549999952316284, -1.754114031791687, -1.7481911182403564, -1.7329657077789307, -1.7050111293792725, -1.6617428064346313, -1.601414680480957, -1.5231214761734009, -1.426798939704895, -1.3132233619689941, -1.1840097904205322, -1.0416152477264404, -0.8893359899520874, -0.731309175491333, -0.5725120306015015, -0.4187622368335724, -0.2767177224159241, -0.15387672185897827, -0.058577895164489746, -1.255276629308355E-7, 0.0, 0.05857766419649124, 0.15387645363807678, 0.2767173945903778, 0.4187619388103485, 0.5725119113922119, 0.7313091158866882, 0.8893360495567322, 1.0416152477264404, 1.1840100288391113, 1.3132234811782837, 1.4267992973327637, 1.5231214761734009, 1.6014143228530884, 1.6617426872253418, 1.7050113677978516, 1.7329657077789307, 1.7481913566589355, 1.7541139125823975, 1.7549999952316284]
	Outline YZ Upper Section View - Z (m): [0.0, 0.05947885662317276, 0.15624375641345978, 0.2809745669364929, 0.42520442605018616, 0.5813197493553162, 0.7425600290298462, 0.903018057346344, 1.0576401948928833, 1.2022255659103394, 1.3334267139434814, 1.4487498998641968, 1.5465539693832397, 1.6260515451431274, 1.6873079538345337, 1.7312424182891846, 1.7596266269683838, 1.7750864028930664, 1.7811001539230347, 1.781999945640564, 1.781999945640564, 1.7811003923416138, 1.7750862836837769, 1.7596266269683838, 1.731242060661316, 1.6873080730438232, 1.6260517835617065, 1.5465539693832397, 1.4487497806549072, 1.3334267139434814, 1.2022253274917603, 1.0576400756835938, 0.903018057346344, 0.7425600290298462, 0.5813199281692505, 0.42520472407341003, 0.2809748947620392, 0.15624406933784485, 0.05947909504175186, 1.2745884703235788E-7]
	Outline YZ Upper Section View - Y (m): [1.7549999952316284, 1.754114031791687, 1.7481911182403564, 1.7329657077789307, 1.7050111293792725, 1.6617428064346313, 1.601414680480957, 1.5231214761734009, 1.426798939704895, 1.3132233619689941, 1.1840097904205322, 1.0416152477264404, 0.8893359899520874, 0.731309175491333, 0.5725120306015015, 0.4187622368335724, 0.2767177224159241, 0.15387672185897827, 0.058577895164489746, 1.255276629308355E-7, 0.0, -0.05857766419649124, -0.15387645363807678, -0.2767173945903778, -0.4187619388103485, -0.5725119113922119, -0.7313091158866882, -0.8893360495567322, -1.0416152477264404, -1.1840100288391113, -1.3132234811782837, -1.4267992973327637, -1.5231214761734009, -1.6014143228530884, -1.6617426872253418, -1.7050113677978516, -1.7329657077789307, -1.7481913566589355, -1.7541139125823975, -1.7549999952316284]
	Outline YZ Upper Section View - Z (m): [0.0, -0.05947885662317276, -0.15624375641345978, -0.2809745669364929, -0.42520442605018616, -0.5813197493553162, -0.7425600290298462, -0.903018057346344, -1.0576401948928833, -1.2022255659103394, -1.3334267139434814, -1.4487498998641968, -1.5465539693832397, -1.6260515451431274, -1.6873079538345337, -1.7312424182891846, -1.7596266269683838, -1.7750864028930664, -1.7811001539230347, -1.781999945640564, -1.781999945640564, -1.7811003923416138, -1.7750862836837769, -1.7596266269683838, -1.731242060661316, -1.6873080730438232, -1.6260517835617065, -1.5465539693832397, -1.4487497806549072, -1.3334267139434814, -1.2022253274917603, -1.0576400756835938, -0.903018057346344, -0.7425600290298462, -0.5813199281692505, -0.42520472407341003, -0.2809748947620392, -0.15624406933784485, -0.05947909504175186, -1.2745884703235788E-7]
	...............................................................................................................
	-------------------------------------
	Lifting surface
	-------------------------------------
	ID: 'JPAD Test Wing DAF - 2016'
	Type: 'WING'
	-------------------------------------
	No. panels = 2
	Main spar position referred to chord = 0.25
	Secondary spar position referred to chord = 0.55
	Surface roughness = 0.00000405 m
	-------------------------------------
	Lifting surface panel
	-------------------------------------
	ID: 'IRON - Inner panel'
	Span = 5.1749999999999989 m
	Lambda_LE = 10.0 deg
	Lambda_c/4 = 9.999999999999996 deg
	Lambda_c/2 = 9.9999999999999929 deg
	Lambda_TE = 9.999999999999989 deg
	Lambda_TE = 9.999999999999989 deg
	.....................................
	                           panel root
	c_r = 4.2527999999999988 m
	epsilon_r = 0.0 deg
	-------------------------------------
	Airfoil
	-------------------------------------
	Name: NACA66_209
	Type: LAMINAR
	t/c = 0.16
	r_le/c = 0.01
	x coordinates = [1.0, 0.993531, 0.982616, 0.970154, 0.956216, 0.941046, 0.924944, 0.908124, 0.890848, 0.873273, 0.855581, 0.837864, 0.820321, 0.803072, 0.786126, 0.76948, 0.753018, 0.736736, 0.720538, 0.704417, 0.688351, 0.672282, 0.656242, 0.640156, 0.624013, 0.607815, 0.59149, 0.575079, 0.558556, 0.541896, 0.525147, 0.508253, 0.491257, 0.474199, 0.457047, 0.43989, 0.422698, 0.405478, 0.388295, 0.371077, 0.353892, 0.336733, 0.319578, 0.302516, 0.285487, 0.268574, 0.251785, 0.235123, 0.218679, 0.202409, 0.186434, 0.17075, 0.155466, 0.140666, 0.126449, 0.112974, 0.100321, 0.088639, 0.077949, 0.068306, 0.059686, 0.052018, 0.045244, 0.039256, 0.033952, 0.02926, 0.025112, 0.02144, 0.018193, 0.015329, 0.012802, 0.010564, 0.008589, 0.006864, 0.005368, 0.004078, 0.002982, 0.002073, 0.001343, 7.83E-4, 3.85E-4, 1.56E-4, 1.04E-4, 2.48E-4, 6.49E-4, 0.00143, 0.002684, 0.004349, 0.006271, 0.008368, 0.01064, 0.013147, 0.015949, 0.019075, 0.022543, 0.026393, 0.030699, 0.035552, 0.041042, 0.047271, 0.054384, 0.062542, 0.071846, 0.082395, 0.094223, 0.107228, 0.121332, 0.13628, 0.151928, 0.168032, 0.18449, 0.201177, 0.218025, 0.235053, 0.252211, 0.269553, 0.286934, 0.304408, 0.321952, 0.339502, 0.357139, 0.37476, 0.392414, 0.410128, 0.427831, 0.44562, 0.463397, 0.481073, 0.498696, 0.516219, 0.533692, 0.551102, 0.56842, 0.585769, 0.603104, 0.620396, 0.637784, 0.655305, 0.672965, 0.690685, 0.70845, 0.726421, 0.744528, 0.762713, 0.780972, 0.799215, 0.817336, 0.835325, 0.853224, 0.870813, 0.887857, 0.904028, 0.919182, 0.933421, 0.946844, 0.959566, 0.971616, 0.982944, 0.993458, 1.0]
	z coordinates = [-0.003551, -0.001905, 0.001009, 0.004454, 0.008426, 0.012861, 0.017685, 0.022827, 0.028176, 0.033666, 0.039242, 0.044833, 0.050367, 0.055725, 0.060872, 0.065745, 0.070357, 0.074699, 0.078767, 0.082584, 0.08612, 0.089402, 0.092419, 0.095161, 0.097661, 0.099897, 0.10189, 0.103656, 0.105177, 0.106487, 0.107577, 0.108451, 0.109144, 0.10963, 0.109933, 0.110057, 0.109976, 0.109726, 0.109284, 0.108648, 0.107844, 0.106836, 0.105657, 0.104293, 0.102733, 0.101008, 0.099072, 0.096962, 0.09465, 0.092135, 0.089437, 0.08652, 0.083441, 0.080162, 0.076755, 0.073215, 0.069605, 0.06596, 0.06232, 0.058763, 0.05529, 0.051963, 0.048774, 0.045699, 0.042752, 0.039898, 0.037094, 0.034323, 0.031573, 0.028837, 0.026126, 0.02346, 0.020844, 0.018276, 0.015759, 0.013299, 0.010897, 0.008553, 0.006265, 0.004038, 0.001871, -2.28E-4, -0.002266, -0.004308, -0.006359, -0.008356, -0.010185, -0.011812, -0.013353, -0.014921, -0.016532, -0.018127, -0.019656, -0.021147, -0.022667, -0.024254, -0.025903, -0.027628, -0.029488, -0.031497, -0.033617, -0.035874, -0.038293, -0.040802, -0.043407, -0.046025, -0.04862, -0.05115, -0.05356, -0.055847, -0.057951, -0.059905, -0.06165, -0.063227, -0.064613, -0.065846, -0.066931, -0.067832, -0.068603, -0.069202, -0.069652, -0.069965, -0.070102, -0.070108, -0.06996, -0.069661, -0.06926, -0.068715, -0.068022, -0.06718, -0.066165, -0.065004, -0.063658, -0.062121, -0.060436, -0.05856, -0.056478, -0.054221, -0.051809, -0.049278, -0.046583, -0.043729, -0.040785, -0.03774, -0.034621, -0.031454, -0.028249, -0.024957, -0.021613, -0.01827, -0.015011, -0.012002, -0.009394, -0.007255, -0.005605, -0.004445, -0.003724, -0.003381, -0.003372, -0.003551]
	alpha_0l = -3.21 deg
	alpha_star = 8.0 deg
	alpha_stall = 18.0 deg
	Cl_alpha = 6.245699999999999 1/rad
	Cl0 = 0.7
	Cl_star = 1.2
	Cl_max = 1.87
	Alpha for Cl curve (deg) = [-30.0 deg, -28.775510204081634 deg, -27.551020408163268 deg, -26.326530612244902 deg, -25.102040816326536 deg, -23.87755102040817 deg, -22.653061224489804 deg, -21.428571428571438 deg, -20.20408163265307 deg, -18.979591836734706 deg, -17.75510204081634 deg, -16.530612244897974 deg, -15.306122448979604 deg, -14.081632653061238 deg, -12.857142857142868 deg, -11.632653061224502 deg, -10.408163265306133 deg, -9.183673469387766 deg, -7.9591836734693988 deg, -6.734693877551031 deg, -5.510204081632663 deg, -4.285714285714295 deg, -3.0612244897959275 deg, -1.8367346938775606 deg, -0.6122448979591932 deg, 0.6122448979591741 deg, 1.8367346938775415 deg, 3.0612244897959089 deg, 4.2857142857142758 deg, 5.5102040816326436 deg, 6.7346938775510115 deg, 7.959183673469379 deg, 9.183673469387745 deg, 10.408163265306115 deg, 11.632653061224481 deg, 12.85714285714285 deg, 14.081632653061217 deg, 15.306122448979586 deg, 16.530612244897952 deg, 17.755102040816318 deg, 18.979591836734684 deg, 20.20408163265305 deg, 21.428571428571416 deg, 22.653061224489782 deg, 23.877551020408148 deg, 25.102040816326515 deg, 26.32653061224488 deg, 27.551020408163247 deg, 28.775510204081613 deg, 30.0 deg]
	Cl curve (deg) = [-2.5702408727542947, -2.436761653458201, -2.3032824341621083, -2.1698032148660147, -2.036323995569921, -1.9028447762738272, -1.7693655569777336, -1.6358863376816404, -1.5024071183855467, -1.3689278990894531, -1.2354486797933597, -1.101969460497266, -0.9684902412011722, -0.8350110219050788, -0.7015318026089847, -0.5680525833128913, -0.43457336401679725, -0.30109414472070384, -0.1676149254246101, -0.03413570612851635, 0.09934351316757739, 0.23282273246367108, 0.36630195175976477, 0.4997811710558584, 0.633260390351952, 0.7667396096480458, 0.9002188289441394, 1.0336980482402331, 1.1671772675363268, 1.3006564868324204, 1.4341357061285143, 1.567614925424608, 1.683890877087232, 1.7668764103367893, 1.8219941751080708, 1.8546882852335598, 1.8704028545457367, 1.874581996877085, 1.8726698260600845, 1.8701104559272181, 1.8723480003109678, 1.88482657304381, 1.912990287958233, 1.9622832588867158, 2.0381495996617387, 2.146033424115786, 2.2913788460813382, 2.4796299793908716, 2.716230937876878, 3.006625835371832]
	Cd_min = 0.0037
	Cl @ Cd_min = 0.7
	k-factor (drag polar) = 0.006
	Cl for Cd curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cd curve (deg) = [0.08584, 0.08049322782174093, 0.07532638067471886, 0.07033945855893374, 0.06553246147438566, 0.06090538942107452, 0.0564582423990004, 0.05219102040816323, 0.04810372344856307, 0.044196351520199885, 0.04046890462307368, 0.036921382757184484, 0.03355378592253226, 0.030366114119117014, 0.027358367346938764, 0.02453054560599749, 0.021882648896293204, 0.0194146772178259, 0.017126630570595575, 0.015018508954602239, 0.01309031236984589, 0.011342040816326525, 0.009773694294044141, 0.008385272802998743, 0.007176776343190331, 0.006148204914618905, 0.005299558517284461, 0.004630837151187003, 0.0041420408163265286, 0.0038331695127030393, 0.003704223240316535, 0.003755201999167015, 0.00398610578925448, 0.0043969346105789285, 0.004987688463140362, 0.00575836734693878, 0.006708971261974182, 0.007839500208246569, 0.00914995418575594, 0.010640333194502295, 0.012310637234485633, 0.014160866305705962, 0.016191020408163274, 0.01840109954185757, 0.020791103706788855, 0.023361032902957116, 0.026110887130362373, 0.029040666389004613, 0.03215037067888383, 0.03544]
	Cm_alpha = 0.0 1/deg
	Cm_ac = -0.18
	Cm_ac @ stall = -0.07
	Cl for Cm curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cm curve (deg) = [-0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07000000000000002, -0.07000000000000002, -0.07000000000000002, -0.07000000000000002, -0.07000000000000003, -0.07000000000000003]
	x_ac/c = 0.26
	M_cr = 0.72	Transition point upper side = 0.6
	Transition point lower side = 0.53

	.....................................
	                            panel tip
	c_t = 4.2527999999999988 m
	epsilon_t = 0.0 deg
	-------------------------------------
	Airfoil
	-------------------------------------
	Name: NACA66_209
	Type: LAMINAR
	t/c = 0.16
	r_le/c = 0.01
	x coordinates = [1.0, 0.993531, 0.982616, 0.970154, 0.956216, 0.941046, 0.924944, 0.908124, 0.890848, 0.873273, 0.855581, 0.837864, 0.820321, 0.803072, 0.786126, 0.76948, 0.753018, 0.736736, 0.720538, 0.704417, 0.688351, 0.672282, 0.656242, 0.640156, 0.624013, 0.607815, 0.59149, 0.575079, 0.558556, 0.541896, 0.525147, 0.508253, 0.491257, 0.474199, 0.457047, 0.43989, 0.422698, 0.405478, 0.388295, 0.371077, 0.353892, 0.336733, 0.319578, 0.302516, 0.285487, 0.268574, 0.251785, 0.235123, 0.218679, 0.202409, 0.186434, 0.17075, 0.155466, 0.140666, 0.126449, 0.112974, 0.100321, 0.088639, 0.077949, 0.068306, 0.059686, 0.052018, 0.045244, 0.039256, 0.033952, 0.02926, 0.025112, 0.02144, 0.018193, 0.015329, 0.012802, 0.010564, 0.008589, 0.006864, 0.005368, 0.004078, 0.002982, 0.002073, 0.001343, 7.83E-4, 3.85E-4, 1.56E-4, 1.04E-4, 2.48E-4, 6.49E-4, 0.00143, 0.002684, 0.004349, 0.006271, 0.008368, 0.01064, 0.013147, 0.015949, 0.019075, 0.022543, 0.026393, 0.030699, 0.035552, 0.041042, 0.047271, 0.054384, 0.062542, 0.071846, 0.082395, 0.094223, 0.107228, 0.121332, 0.13628, 0.151928, 0.168032, 0.18449, 0.201177, 0.218025, 0.235053, 0.252211, 0.269553, 0.286934, 0.304408, 0.321952, 0.339502, 0.357139, 0.37476, 0.392414, 0.410128, 0.427831, 0.44562, 0.463397, 0.481073, 0.498696, 0.516219, 0.533692, 0.551102, 0.56842, 0.585769, 0.603104, 0.620396, 0.637784, 0.655305, 0.672965, 0.690685, 0.70845, 0.726421, 0.744528, 0.762713, 0.780972, 0.799215, 0.817336, 0.835325, 0.853224, 0.870813, 0.887857, 0.904028, 0.919182, 0.933421, 0.946844, 0.959566, 0.971616, 0.982944, 0.993458, 1.0]
	z coordinates = [-0.003551, -0.001905, 0.001009, 0.004454, 0.008426, 0.012861, 0.017685, 0.022827, 0.028176, 0.033666, 0.039242, 0.044833, 0.050367, 0.055725, 0.060872, 0.065745, 0.070357, 0.074699, 0.078767, 0.082584, 0.08612, 0.089402, 0.092419, 0.095161, 0.097661, 0.099897, 0.10189, 0.103656, 0.105177, 0.106487, 0.107577, 0.108451, 0.109144, 0.10963, 0.109933, 0.110057, 0.109976, 0.109726, 0.109284, 0.108648, 0.107844, 0.106836, 0.105657, 0.104293, 0.102733, 0.101008, 0.099072, 0.096962, 0.09465, 0.092135, 0.089437, 0.08652, 0.083441, 0.080162, 0.076755, 0.073215, 0.069605, 0.06596, 0.06232, 0.058763, 0.05529, 0.051963, 0.048774, 0.045699, 0.042752, 0.039898, 0.037094, 0.034323, 0.031573, 0.028837, 0.026126, 0.02346, 0.020844, 0.018276, 0.015759, 0.013299, 0.010897, 0.008553, 0.006265, 0.004038, 0.001871, -2.28E-4, -0.002266, -0.004308, -0.006359, -0.008356, -0.010185, -0.011812, -0.013353, -0.014921, -0.016532, -0.018127, -0.019656, -0.021147, -0.022667, -0.024254, -0.025903, -0.027628, -0.029488, -0.031497, -0.033617, -0.035874, -0.038293, -0.040802, -0.043407, -0.046025, -0.04862, -0.05115, -0.05356, -0.055847, -0.057951, -0.059905, -0.06165, -0.063227, -0.064613, -0.065846, -0.066931, -0.067832, -0.068603, -0.069202, -0.069652, -0.069965, -0.070102, -0.070108, -0.06996, -0.069661, -0.06926, -0.068715, -0.068022, -0.06718, -0.066165, -0.065004, -0.063658, -0.062121, -0.060436, -0.05856, -0.056478, -0.054221, -0.051809, -0.049278, -0.046583, -0.043729, -0.040785, -0.03774, -0.034621, -0.031454, -0.028249, -0.024957, -0.021613, -0.01827, -0.015011, -0.012002, -0.009394, -0.007255, -0.005605, -0.004445, -0.003724, -0.003381, -0.003372, -0.003551]
	alpha_0l = -3.21 deg
	alpha_star = 8.0 deg
	alpha_stall = 18.0 deg
	Cl_alpha = 6.245699999999999 1/rad
	Cl0 = 0.7
	Cl_star = 1.2
	Cl_max = 1.87
	Alpha for Cl curve (deg) = [-30.0 deg, -28.775510204081634 deg, -27.551020408163268 deg, -26.326530612244902 deg, -25.102040816326536 deg, -23.87755102040817 deg, -22.653061224489804 deg, -21.428571428571438 deg, -20.20408163265307 deg, -18.979591836734706 deg, -17.75510204081634 deg, -16.530612244897974 deg, -15.306122448979604 deg, -14.081632653061238 deg, -12.857142857142868 deg, -11.632653061224502 deg, -10.408163265306133 deg, -9.183673469387766 deg, -7.9591836734693988 deg, -6.734693877551031 deg, -5.510204081632663 deg, -4.285714285714295 deg, -3.0612244897959275 deg, -1.8367346938775606 deg, -0.6122448979591932 deg, 0.6122448979591741 deg, 1.8367346938775415 deg, 3.0612244897959089 deg, 4.2857142857142758 deg, 5.5102040816326436 deg, 6.7346938775510115 deg, 7.959183673469379 deg, 9.183673469387745 deg, 10.408163265306115 deg, 11.632653061224481 deg, 12.85714285714285 deg, 14.081632653061217 deg, 15.306122448979586 deg, 16.530612244897952 deg, 17.755102040816318 deg, 18.979591836734684 deg, 20.20408163265305 deg, 21.428571428571416 deg, 22.653061224489782 deg, 23.877551020408148 deg, 25.102040816326515 deg, 26.32653061224488 deg, 27.551020408163247 deg, 28.775510204081613 deg, 30.0 deg]
	Cl curve (deg) = [-2.5702408727542947, -2.436761653458201, -2.3032824341621083, -2.1698032148660147, -2.036323995569921, -1.9028447762738272, -1.7693655569777336, -1.6358863376816404, -1.5024071183855467, -1.3689278990894531, -1.2354486797933597, -1.101969460497266, -0.9684902412011722, -0.8350110219050788, -0.7015318026089847, -0.5680525833128913, -0.43457336401679725, -0.30109414472070384, -0.1676149254246101, -0.03413570612851635, 0.09934351316757739, 0.23282273246367108, 0.36630195175976477, 0.4997811710558584, 0.633260390351952, 0.7667396096480458, 0.9002188289441394, 1.0336980482402331, 1.1671772675363268, 1.3006564868324204, 1.4341357061285143, 1.567614925424608, 1.683890877087232, 1.7668764103367893, 1.8219941751080708, 1.8546882852335598, 1.8704028545457367, 1.874581996877085, 1.8726698260600845, 1.8701104559272181, 1.8723480003109678, 1.88482657304381, 1.912990287958233, 1.9622832588867158, 2.0381495996617387, 2.146033424115786, 2.2913788460813382, 2.4796299793908716, 2.716230937876878, 3.006625835371832]
	Cd_min = 0.0037
	Cl @ Cd_min = 0.7
	k-factor (drag polar) = 0.006
	Cl for Cd curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cd curve (deg) = [0.08584, 0.08049322782174093, 0.07532638067471886, 0.07033945855893374, 0.06553246147438566, 0.06090538942107452, 0.0564582423990004, 0.05219102040816323, 0.04810372344856307, 0.044196351520199885, 0.04046890462307368, 0.036921382757184484, 0.03355378592253226, 0.030366114119117014, 0.027358367346938764, 0.02453054560599749, 0.021882648896293204, 0.0194146772178259, 0.017126630570595575, 0.015018508954602239, 0.01309031236984589, 0.011342040816326525, 0.009773694294044141, 0.008385272802998743, 0.007176776343190331, 0.006148204914618905, 0.005299558517284461, 0.004630837151187003, 0.0041420408163265286, 0.0038331695127030393, 0.003704223240316535, 0.003755201999167015, 0.00398610578925448, 0.0043969346105789285, 0.004987688463140362, 0.00575836734693878, 0.006708971261974182, 0.007839500208246569, 0.00914995418575594, 0.010640333194502295, 0.012310637234485633, 0.014160866305705962, 0.016191020408163274, 0.01840109954185757, 0.020791103706788855, 0.023361032902957116, 0.026110887130362373, 0.029040666389004613, 0.03215037067888383, 0.03544]
	Cm_alpha = 0.0 1/deg
	Cm_ac = -0.18
	Cm_ac @ stall = -0.07
	Cl for Cm curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cm curve (deg) = [-0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07000000000000002, -0.07000000000000002, -0.07000000000000002, -0.07000000000000002, -0.07000000000000003, -0.07000000000000003]
	x_ac/c = 0.26
	M_cr = 0.72	Transition point upper side = 0.6
	Transition point lower side = 0.53

	.....................................
	                   panel derived data
	S = 19.57391999999999 m²
	S_wet = 39.147839999999974 m²
	lambda = 0.9999999999999999
	AR = 1.3681789340101524
	c_MAC = 4.252799999999997 m
	X_LE_MAC = 0.2281230312915764 m
	Y_LE_MAC = 1.2937499999999995 m
	Z_LE_MAC = 0.12457395610556553 m
	-------------------------------------
	Lifting surface panel
	-------------------------------------
	ID: 'IRON - Outer panel'
	Span = 12.074999999999999 m
	Lambda_LE = 10.0 deg
	Lambda_c/4 = 9.999999999999996 deg
	Lambda_c/2 = 9.999999999999996 deg
	Lambda_TE = 9.999999999999994 deg
	Lambda_TE = 9.999999999999994 deg
	.....................................
	                           panel root
	c_r = 3.3119999999999994 m
	epsilon_r = -0.0000000000000002220446049250313 deg
	-------------------------------------
	Airfoil
	-------------------------------------
	Name: NACA66_209
	Type: LAMINAR
	t/c = 0.16
	r_le/c = 0.01
	x coordinates = [1.0, 0.993531, 0.982616, 0.970154, 0.956216, 0.941046, 0.924944, 0.908124, 0.890848, 0.873273, 0.855581, 0.837864, 0.820321, 0.803072, 0.786126, 0.76948, 0.753018, 0.736736, 0.720538, 0.704417, 0.688351, 0.672282, 0.656242, 0.640156, 0.624013, 0.607815, 0.59149, 0.575079, 0.558556, 0.541896, 0.525147, 0.508253, 0.491257, 0.474199, 0.457047, 0.43989, 0.422698, 0.405478, 0.388295, 0.371077, 0.353892, 0.336733, 0.319578, 0.302516, 0.285487, 0.268574, 0.251785, 0.235123, 0.218679, 0.202409, 0.186434, 0.17075, 0.155466, 0.140666, 0.126449, 0.112974, 0.100321, 0.088639, 0.077949, 0.068306, 0.059686, 0.052018, 0.045244, 0.039256, 0.033952, 0.02926, 0.025112, 0.02144, 0.018193, 0.015329, 0.012802, 0.010564, 0.008589, 0.006864, 0.005368, 0.004078, 0.002982, 0.002073, 0.001343, 7.83E-4, 3.85E-4, 1.56E-4, 1.04E-4, 2.48E-4, 6.49E-4, 0.00143, 0.002684, 0.004349, 0.006271, 0.008368, 0.01064, 0.013147, 0.015949, 0.019075, 0.022543, 0.026393, 0.030699, 0.035552, 0.041042, 0.047271, 0.054384, 0.062542, 0.071846, 0.082395, 0.094223, 0.107228, 0.121332, 0.13628, 0.151928, 0.168032, 0.18449, 0.201177, 0.218025, 0.235053, 0.252211, 0.269553, 0.286934, 0.304408, 0.321952, 0.339502, 0.357139, 0.37476, 0.392414, 0.410128, 0.427831, 0.44562, 0.463397, 0.481073, 0.498696, 0.516219, 0.533692, 0.551102, 0.56842, 0.585769, 0.603104, 0.620396, 0.637784, 0.655305, 0.672965, 0.690685, 0.70845, 0.726421, 0.744528, 0.762713, 0.780972, 0.799215, 0.817336, 0.835325, 0.853224, 0.870813, 0.887857, 0.904028, 0.919182, 0.933421, 0.946844, 0.959566, 0.971616, 0.982944, 0.993458, 1.0]
	z coordinates = [-0.003551, -0.001905, 0.001009, 0.004454, 0.008426, 0.012861, 0.017685, 0.022827, 0.028176, 0.033666, 0.039242, 0.044833, 0.050367, 0.055725, 0.060872, 0.065745, 0.070357, 0.074699, 0.078767, 0.082584, 0.08612, 0.089402, 0.092419, 0.095161, 0.097661, 0.099897, 0.10189, 0.103656, 0.105177, 0.106487, 0.107577, 0.108451, 0.109144, 0.10963, 0.109933, 0.110057, 0.109976, 0.109726, 0.109284, 0.108648, 0.107844, 0.106836, 0.105657, 0.104293, 0.102733, 0.101008, 0.099072, 0.096962, 0.09465, 0.092135, 0.089437, 0.08652, 0.083441, 0.080162, 0.076755, 0.073215, 0.069605, 0.06596, 0.06232, 0.058763, 0.05529, 0.051963, 0.048774, 0.045699, 0.042752, 0.039898, 0.037094, 0.034323, 0.031573, 0.028837, 0.026126, 0.02346, 0.020844, 0.018276, 0.015759, 0.013299, 0.010897, 0.008553, 0.006265, 0.004038, 0.001871, -2.28E-4, -0.002266, -0.004308, -0.006359, -0.008356, -0.010185, -0.011812, -0.013353, -0.014921, -0.016532, -0.018127, -0.019656, -0.021147, -0.022667, -0.024254, -0.025903, -0.027628, -0.029488, -0.031497, -0.033617, -0.035874, -0.038293, -0.040802, -0.043407, -0.046025, -0.04862, -0.05115, -0.05356, -0.055847, -0.057951, -0.059905, -0.06165, -0.063227, -0.064613, -0.065846, -0.066931, -0.067832, -0.068603, -0.069202, -0.069652, -0.069965, -0.070102, -0.070108, -0.06996, -0.069661, -0.06926, -0.068715, -0.068022, -0.06718, -0.066165, -0.065004, -0.063658, -0.062121, -0.060436, -0.05856, -0.056478, -0.054221, -0.051809, -0.049278, -0.046583, -0.043729, -0.040785, -0.03774, -0.034621, -0.031454, -0.028249, -0.024957, -0.021613, -0.01827, -0.015011, -0.012002, -0.009394, -0.007255, -0.005605, -0.004445, -0.003724, -0.003381, -0.003372, -0.003551]
	alpha_0l = -3.21 deg
	alpha_star = 8.0 deg
	alpha_stall = 18.0 deg
	Cl_alpha = 6.245699999999999 1/rad
	Cl0 = 0.7
	Cl_star = 1.2
	Cl_max = 1.87
	Alpha for Cl curve (deg) = [-30.0 deg, -28.775510204081634 deg, -27.551020408163268 deg, -26.326530612244902 deg, -25.102040816326536 deg, -23.87755102040817 deg, -22.653061224489804 deg, -21.428571428571438 deg, -20.20408163265307 deg, -18.979591836734706 deg, -17.75510204081634 deg, -16.530612244897974 deg, -15.306122448979604 deg, -14.081632653061238 deg, -12.857142857142868 deg, -11.632653061224502 deg, -10.408163265306133 deg, -9.183673469387766 deg, -7.9591836734693988 deg, -6.734693877551031 deg, -5.510204081632663 deg, -4.285714285714295 deg, -3.0612244897959275 deg, -1.8367346938775606 deg, -0.6122448979591932 deg, 0.6122448979591741 deg, 1.8367346938775415 deg, 3.0612244897959089 deg, 4.2857142857142758 deg, 5.5102040816326436 deg, 6.7346938775510115 deg, 7.959183673469379 deg, 9.183673469387745 deg, 10.408163265306115 deg, 11.632653061224481 deg, 12.85714285714285 deg, 14.081632653061217 deg, 15.306122448979586 deg, 16.530612244897952 deg, 17.755102040816318 deg, 18.979591836734684 deg, 20.20408163265305 deg, 21.428571428571416 deg, 22.653061224489782 deg, 23.877551020408148 deg, 25.102040816326515 deg, 26.32653061224488 deg, 27.551020408163247 deg, 28.775510204081613 deg, 30.0 deg]
	Cl curve (deg) = [-2.5702408727542947, -2.436761653458201, -2.3032824341621083, -2.1698032148660147, -2.036323995569921, -1.9028447762738272, -1.7693655569777336, -1.6358863376816404, -1.5024071183855467, -1.3689278990894531, -1.2354486797933597, -1.101969460497266, -0.9684902412011722, -0.8350110219050788, -0.7015318026089847, -0.5680525833128913, -0.43457336401679725, -0.30109414472070384, -0.1676149254246101, -0.03413570612851635, 0.09934351316757739, 0.23282273246367108, 0.36630195175976477, 0.4997811710558584, 0.633260390351952, 0.7667396096480458, 0.9002188289441394, 1.0336980482402331, 1.1671772675363268, 1.3006564868324204, 1.4341357061285143, 1.567614925424608, 1.683890877087232, 1.7668764103367893, 1.8219941751080708, 1.8546882852335598, 1.8704028545457367, 1.874581996877085, 1.8726698260600845, 1.8701104559272181, 1.8723480003109678, 1.88482657304381, 1.912990287958233, 1.9622832588867158, 2.0381495996617387, 2.146033424115786, 2.2913788460813382, 2.4796299793908716, 2.716230937876878, 3.006625835371832]
	Cd_min = 0.0037
	Cl @ Cd_min = 0.7
	k-factor (drag polar) = 0.006
	Cl for Cd curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cd curve (deg) = [0.08584, 0.08049322782174093, 0.07532638067471886, 0.07033945855893374, 0.06553246147438566, 0.06090538942107452, 0.0564582423990004, 0.05219102040816323, 0.04810372344856307, 0.044196351520199885, 0.04046890462307368, 0.036921382757184484, 0.03355378592253226, 0.030366114119117014, 0.027358367346938764, 0.02453054560599749, 0.021882648896293204, 0.0194146772178259, 0.017126630570595575, 0.015018508954602239, 0.01309031236984589, 0.011342040816326525, 0.009773694294044141, 0.008385272802998743, 0.007176776343190331, 0.006148204914618905, 0.005299558517284461, 0.004630837151187003, 0.0041420408163265286, 0.0038331695127030393, 0.003704223240316535, 0.003755201999167015, 0.00398610578925448, 0.0043969346105789285, 0.004987688463140362, 0.00575836734693878, 0.006708971261974182, 0.007839500208246569, 0.00914995418575594, 0.010640333194502295, 0.012310637234485633, 0.014160866305705962, 0.016191020408163274, 0.01840109954185757, 0.020791103706788855, 0.023361032902957116, 0.026110887130362373, 0.029040666389004613, 0.03215037067888383, 0.03544]
	Cm_alpha = 0.0 1/deg
	Cm_ac = -0.18
	Cm_ac @ stall = -0.07
	Cl for Cm curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cm curve (deg) = [-0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07000000000000002, -0.07000000000000002, -0.07000000000000002, -0.07000000000000002, -0.07000000000000003, -0.07000000000000003]
	x_ac/c = 0.26
	M_cr = 0.72	Transition point upper side = 0.6
	Transition point lower side = 0.53

	.....................................
	                            panel tip
	c_t = 3.3119999999999994 m
	epsilon_t = -0.0000000000000002220446049250313 deg
	-------------------------------------
	Airfoil
	-------------------------------------
	Name: NACA66_209
	Type: LAMINAR
	t/c = 0.14
	r_le/c = 0.01
	x coordinates = [1.0, 0.994006, 0.983386, 0.970838, 0.956749, 0.941664, 0.926069, 0.910206, 0.894206, 0.878188, 0.862181, 0.846135, 0.830169, 0.814353, 0.798675, 0.783203, 0.767887, 0.75264, 0.737487, 0.722361, 0.707239, 0.692153, 0.677029, 0.661927, 0.646819, 0.631622, 0.61641, 0.601129, 0.585763, 0.570377, 0.554889, 0.539335, 0.523758, 0.508071, 0.492338, 0.476598, 0.460783, 0.444983, 0.4292, 0.41334, 0.397526, 0.381718, 0.365856, 0.350067, 0.334254, 0.318437, 0.302698, 0.286939, 0.271235, 0.255626, 0.240016, 0.224544, 0.209135, 0.193824, 0.178699, 0.163656, 0.148894, 0.134303, 0.120093, 0.106264, 0.093014, 0.080466, 0.068817, 0.058277, 0.048968, 0.04095, 0.034107, 0.028318, 0.023422, 0.019268, 0.015742, 0.012736, 0.010163, 0.007973, 0.006131, 0.004588, 0.003305, 0.002258, 0.001429, 8.04E-4, 3.67E-4, 1.34E-4, 1.24E-4, 3.85E-4, 0.001067, 0.002323, 0.004054, 0.006076, 0.008322, 0.010813, 0.013638, 0.016901, 0.020701, 0.025156, 0.030445, 0.03683, 0.044552, 0.053784, 0.064671, 0.076984, 0.090477, 0.104731, 0.119555, 0.134719, 0.150121, 0.165678, 0.181294, 0.197029, 0.212727, 0.228544, 0.244373, 0.260305, 0.276313, 0.292258, 0.308313, 0.324361, 0.34039, 0.356505, 0.372578, 0.388641, 0.40479, 0.420893, 0.437035, 0.453272, 0.469419, 0.485522, 0.50161, 0.517623, 0.533645, 0.549641, 0.56555, 0.581512, 0.597505, 0.613415, 0.629357, 0.645398, 0.66153, 0.67775, 0.693923, 0.710115, 0.726467, 0.742884, 0.759307, 0.775785, 0.792255, 0.808645, 0.824889, 0.841141, 0.857372, 0.873509, 0.889399, 0.904773, 0.919496, 0.933608, 0.94713, 0.960087, 0.972396, 0.983792, 0.993971, 1.0]
	z coordinates = [-0.003551, -0.002179, 3.36E-4, 0.00337, 0.006834, 0.01058, 0.014491, 0.018507, 0.02258, 0.026678, 0.030812, 0.034976, 0.039128, 0.043224, 0.04722, 0.05107, 0.054741, 0.058241, 0.061558, 0.064679, 0.067625, 0.070369, 0.072928, 0.075295, 0.077451, 0.079424, 0.08121, 0.082806, 0.084234, 0.085486, 0.086567, 0.087501, 0.088274, 0.088896, 0.089393, 0.089745, 0.089969, 0.090072, 0.090032, 0.089867, 0.089585, 0.089164, 0.08862, 0.087959, 0.087155, 0.086239, 0.085195, 0.08401, 0.082716, 0.081272, 0.079693, 0.077978, 0.076102, 0.074082, 0.071897, 0.069537, 0.067014, 0.064293, 0.061408, 0.058329, 0.055095, 0.051707, 0.04825, 0.044773, 0.041397, 0.038155, 0.035079, 0.032155, 0.029325, 0.02656, 0.023842, 0.021184, 0.018614, 0.016132, 0.013724, 0.011397, 0.009156, 0.006998, 0.00492, 0.00292, 9.99E-4, -8.45E-4, -0.002625, -0.004408, -0.006138, -0.00762, -0.008786, -0.009835, -0.010945, -0.012144, -0.013347, -0.014503, -0.015682, -0.016979, -0.018414, -0.020007, -0.02184, -0.023856, -0.026013, -0.028252, -0.030466, -0.032594, -0.034597, -0.036481, -0.038218, -0.039846, -0.04132, -0.042688, -0.043908, -0.045006, -0.04598, -0.046836, -0.047605, -0.048264, -0.048812, -0.049282, -0.049637, -0.049901, -0.050085, -0.050153, -0.050139, -0.050038, -0.049835, -0.049562, -0.049224, -0.048791, -0.04827, -0.047653, -0.046925, -0.046111, -0.045183, -0.044129, -0.042985, -0.041738, -0.040364, -0.038878, -0.037299, -0.035652, -0.03395, -0.032155, -0.030283, -0.028382, -0.026443, -0.024472, -0.022487, -0.020493, -0.018462, -0.016363, -0.014223, -0.012053, -0.009906, -0.007901, -0.006158, -0.004753, -0.003726, -0.003105, -0.002855, -0.002918, -0.003229, -0.003551]
	alpha_0l = -3.0 deg
	alpha_star = 10.0 deg
	alpha_stall = 17.0 deg
	Cl_alpha = 6.245699999999999 1/rad
	Cl0 = 0.37
	Cl_star = 1.2
	Cl_max = 1.55
	Alpha for Cl curve (deg) = [-30.0 deg, -28.775510204081634 deg, -27.551020408163268 deg, -26.326530612244902 deg, -25.102040816326536 deg, -23.87755102040817 deg, -22.653061224489804 deg, -21.428571428571438 deg, -20.20408163265307 deg, -18.979591836734706 deg, -17.75510204081634 deg, -16.530612244897974 deg, -15.306122448979604 deg, -14.081632653061238 deg, -12.857142857142868 deg, -11.632653061224502 deg, -10.408163265306133 deg, -9.183673469387766 deg, -7.9591836734693988 deg, -6.734693877551031 deg, -5.510204081632663 deg, -4.285714285714295 deg, -3.0612244897959275 deg, -1.8367346938775606 deg, -0.6122448979591932 deg, 0.6122448979591741 deg, 1.8367346938775415 deg, 3.0612244897959089 deg, 4.2857142857142758 deg, 5.5102040816326436 deg, 6.7346938775510115 deg, 7.959183673469379 deg, 9.183673469387745 deg, 10.408163265306115 deg, 11.632653061224481 deg, 12.85714285714285 deg, 14.081632653061217 deg, 15.306122448979586 deg, 16.530612244897952 deg, 17.755102040816318 deg, 18.979591836734684 deg, 20.20408163265305 deg, 21.428571428571416 deg, 22.653061224489782 deg, 23.877551020408148 deg, 25.102040816326515 deg, 26.32653061224488 deg, 27.551020408163247 deg, 28.775510204081613 deg, 30.0 deg]
	Cl curve (deg) = [-2.9002408727542948, -2.766761653458201, -2.633282434162108, -2.4998032148660143, -2.3663239955699207, -2.232844776273827, -2.0993655569777334, -1.9658863376816402, -1.8324071183855466, -1.698927899089453, -1.5654486797933598, -1.4319694604972661, -1.298490241201172, -1.1650110219050789, -1.0315318026089848, -0.8980525833128913, -0.7645733640167972, -0.6310941447207038, -0.49761492542461006, -0.3641357061285163, -0.23065648683242257, -0.09717726753632888, 0.036301951759764806, 0.16978117105585844, 0.3032603903519521, 0.4367396096480458, 0.5702188289441394, 0.7036980482402331, 0.8371772675363267, 0.9706564868324205, 1.1041357061285142, 1.2376149254246078, 1.3710941447207015, 1.5004174545899738, 1.5771078522463982, 1.6018848867410544, 1.5934791997729758, 1.5706214330411883, 1.5520422282447286, 1.5564722270826352, 1.6026420712539342, 1.7092824024576623, 1.8951238623928561, 2.178897092758542, 2.579332735253756, 3.1151614315775427, 3.805113823428917, 4.667920552506926, 5.722312260510593, 6.987019589138976]
	Cd_min = 0.0037
	Cl @ Cd_min = 0.5
	k-factor (drag polar) = 0.006
	Cl for Cd curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cd curve (deg) = [0.07719999999999999, 0.07214710537276134, 0.06727413577675967, 0.06258109121199498, 0.05806797167846729, 0.05373477717617657, 0.04958150770512284, 0.04560816326530609, 0.04181474385672634, 0.038201249479383574, 0.03476768013327778, 0.03151403581840897, 0.028440316534777153, 0.025546522282382328, 0.022832653061224478, 0.02029870887130361, 0.017944689712619734, 0.01577059558517284, 0.013776426488962925, 0.01196218242399, 0.010327863390254054, 0.008873469387755097, 0.007599000416493123, 0.0065044564764681345, 0.005589837567680129, 0.00485514369012911, 0.004300374843815075, 0.0039255310287380244, 0.003730612244897959, 0.0037156184922948776, 0.0038805497709287814, 0.004225406080799669, 0.004750187421907542, 0.0054548937942524, 0.006339525197834241, 0.007404081632653067, 0.008648563098708876, 0.010072969596001671, 0.01167730112453145, 0.013461557684298213, 0.015425739275301959, 0.017569845897542694, 0.019893877551020414, 0.022397834235735124, 0.02508171595168681, 0.027945522698875493, 0.03098925447730115, 0.0342129112869638, 0.03761649312786343, 0.0412]
	Cm_alpha = 0.0 1/deg
	Cm_ac = -0.08
	Cm_ac @ stall = -0.05
	Cl for Cm curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cm curve (deg) = [-0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.049999999999999996, -0.04999999999999999, -0.04999999999999998, -0.04999999999999997, -0.04999999999999995, -0.049999999999999926, -0.049999999999999906, -0.04999999999999987, -0.049999999999999836, -0.049999999999999795, -0.049999999999999746]
	x_ac/c = 0.25
	M_cr = 0.76	Transition point upper side = 0.6
	Transition point lower side = 0.6

	.....................................
	                   panel derived data
	S = 29.559599999999989 m²
	S_wet = 59.11919999999997 m²
	lambda = 0.9999999999999999
	AR = 4.932598039215686
	c_MAC = 3.3119999999999985 m
	X_LE_MAC = 0.53228707301367828 m
	Y_LE_MAC = 3.0187499999999989 m
	Z_LE_MAC = 0.2906725642463196 m
	---------------------------------------
	Equivalent wing
	---------------------------------------
	-------------------------------------
	Lifting surface panel
	-------------------------------------
	ID: 'Equivalent Wing Panel'
	Span = 17.17058442183383 m
	Lambda_LE = 9.999999999999994 deg
	Lambda_c/4 = 9.9999999999999929 deg
	Lambda_c/2 = 9.9999999999999929 deg
	Lambda_TE = 9.9999999999999929 deg
	Lambda_TE = 9.9999999999999929 deg
	.....................................
	                           panel root
	c_r = 4.119248842650833 m
	epsilon_r = 0.0 deg
	-------------------------------------
	Airfoil
	-------------------------------------
	Name: NACA66_209
	Type: LAMINAR
	t/c = 0.16
	r_le/c = 0.01
	x coordinates = [1.0, 0.993531, 0.982616, 0.970154, 0.956216, 0.941046, 0.924944, 0.908124, 0.890848, 0.873273, 0.855581, 0.837864, 0.820321, 0.803072, 0.786126, 0.76948, 0.753018, 0.736736, 0.720538, 0.704417, 0.688351, 0.672282, 0.656242, 0.640156, 0.624013, 0.607815, 0.59149, 0.575079, 0.558556, 0.541896, 0.525147, 0.508253, 0.491257, 0.474199, 0.457047, 0.43989, 0.422698, 0.405478, 0.388295, 0.371077, 0.353892, 0.336733, 0.319578, 0.302516, 0.285487, 0.268574, 0.251785, 0.235123, 0.218679, 0.202409, 0.186434, 0.17075, 0.155466, 0.140666, 0.126449, 0.112974, 0.100321, 0.088639, 0.077949, 0.068306, 0.059686, 0.052018, 0.045244, 0.039256, 0.033952, 0.02926, 0.025112, 0.02144, 0.018193, 0.015329, 0.012802, 0.010564, 0.008589, 0.006864, 0.005368, 0.004078, 0.002982, 0.002073, 0.001343, 7.83E-4, 3.85E-4, 1.56E-4, 1.04E-4, 2.48E-4, 6.49E-4, 0.00143, 0.002684, 0.004349, 0.006271, 0.008368, 0.01064, 0.013147, 0.015949, 0.019075, 0.022543, 0.026393, 0.030699, 0.035552, 0.041042, 0.047271, 0.054384, 0.062542, 0.071846, 0.082395, 0.094223, 0.107228, 0.121332, 0.13628, 0.151928, 0.168032, 0.18449, 0.201177, 0.218025, 0.235053, 0.252211, 0.269553, 0.286934, 0.304408, 0.321952, 0.339502, 0.357139, 0.37476, 0.392414, 0.410128, 0.427831, 0.44562, 0.463397, 0.481073, 0.498696, 0.516219, 0.533692, 0.551102, 0.56842, 0.585769, 0.603104, 0.620396, 0.637784, 0.655305, 0.672965, 0.690685, 0.70845, 0.726421, 0.744528, 0.762713, 0.780972, 0.799215, 0.817336, 0.835325, 0.853224, 0.870813, 0.887857, 0.904028, 0.919182, 0.933421, 0.946844, 0.959566, 0.971616, 0.982944, 0.993458, 1.0]
	z coordinates = [-0.003551, -0.001905, 0.001009, 0.004454, 0.008426, 0.012861, 0.017685, 0.022827, 0.028176, 0.033666, 0.039242, 0.044833, 0.050367, 0.055725, 0.060872, 0.065745, 0.070357, 0.074699, 0.078767, 0.082584, 0.08612, 0.089402, 0.092419, 0.095161, 0.097661, 0.099897, 0.10189, 0.103656, 0.105177, 0.106487, 0.107577, 0.108451, 0.109144, 0.10963, 0.109933, 0.110057, 0.109976, 0.109726, 0.109284, 0.108648, 0.107844, 0.106836, 0.105657, 0.104293, 0.102733, 0.101008, 0.099072, 0.096962, 0.09465, 0.092135, 0.089437, 0.08652, 0.083441, 0.080162, 0.076755, 0.073215, 0.069605, 0.06596, 0.06232, 0.058763, 0.05529, 0.051963, 0.048774, 0.045699, 0.042752, 0.039898, 0.037094, 0.034323, 0.031573, 0.028837, 0.026126, 0.02346, 0.020844, 0.018276, 0.015759, 0.013299, 0.010897, 0.008553, 0.006265, 0.004038, 0.001871, -2.28E-4, -0.002266, -0.004308, -0.006359, -0.008356, -0.010185, -0.011812, -0.013353, -0.014921, -0.016532, -0.018127, -0.019656, -0.021147, -0.022667, -0.024254, -0.025903, -0.027628, -0.029488, -0.031497, -0.033617, -0.035874, -0.038293, -0.040802, -0.043407, -0.046025, -0.04862, -0.05115, -0.05356, -0.055847, -0.057951, -0.059905, -0.06165, -0.063227, -0.064613, -0.065846, -0.066931, -0.067832, -0.068603, -0.069202, -0.069652, -0.069965, -0.070102, -0.070108, -0.06996, -0.069661, -0.06926, -0.068715, -0.068022, -0.06718, -0.066165, -0.065004, -0.063658, -0.062121, -0.060436, -0.05856, -0.056478, -0.054221, -0.051809, -0.049278, -0.046583, -0.043729, -0.040785, -0.03774, -0.034621, -0.031454, -0.028249, -0.024957, -0.021613, -0.01827, -0.015011, -0.012002, -0.009394, -0.007255, -0.005605, -0.004445, -0.003724, -0.003381, -0.003372, -0.003551]
	alpha_0l = -3.21 deg
	alpha_star = 8.0 deg
	alpha_stall = 18.0 deg
	Cl_alpha = 6.245699999999999 1/rad
	Cl0 = 0.7
	Cl_star = 1.2
	Cl_max = 1.87
	Alpha for Cl curve (deg) = [-30.0 deg, -28.775510204081634 deg, -27.551020408163268 deg, -26.326530612244902 deg, -25.102040816326536 deg, -23.87755102040817 deg, -22.653061224489804 deg, -21.428571428571438 deg, -20.20408163265307 deg, -18.979591836734706 deg, -17.75510204081634 deg, -16.530612244897974 deg, -15.306122448979604 deg, -14.081632653061238 deg, -12.857142857142868 deg, -11.632653061224502 deg, -10.408163265306133 deg, -9.183673469387766 deg, -7.9591836734693988 deg, -6.734693877551031 deg, -5.510204081632663 deg, -4.285714285714295 deg, -3.0612244897959275 deg, -1.8367346938775606 deg, -0.6122448979591932 deg, 0.6122448979591741 deg, 1.8367346938775415 deg, 3.0612244897959089 deg, 4.2857142857142758 deg, 5.5102040816326436 deg, 6.7346938775510115 deg, 7.959183673469379 deg, 9.183673469387745 deg, 10.408163265306115 deg, 11.632653061224481 deg, 12.85714285714285 deg, 14.081632653061217 deg, 15.306122448979586 deg, 16.530612244897952 deg, 17.755102040816318 deg, 18.979591836734684 deg, 20.20408163265305 deg, 21.428571428571416 deg, 22.653061224489782 deg, 23.877551020408148 deg, 25.102040816326515 deg, 26.32653061224488 deg, 27.551020408163247 deg, 28.775510204081613 deg, 30.0 deg]
	Cl curve (deg) = [-2.5702408727542947, -2.436761653458201, -2.3032824341621083, -2.1698032148660147, -2.036323995569921, -1.9028447762738272, -1.7693655569777336, -1.6358863376816404, -1.5024071183855467, -1.3689278990894531, -1.2354486797933597, -1.101969460497266, -0.9684902412011722, -0.8350110219050788, -0.7015318026089847, -0.5680525833128913, -0.43457336401679725, -0.30109414472070384, -0.1676149254246101, -0.03413570612851635, 0.09934351316757739, 0.23282273246367108, 0.36630195175976477, 0.4997811710558584, 0.633260390351952, 0.7667396096480458, 0.9002188289441394, 1.0336980482402331, 1.1671772675363268, 1.3006564868324204, 1.4341357061285143, 1.567614925424608, 1.683890877087232, 1.7668764103367893, 1.8219941751080708, 1.8546882852335598, 1.8704028545457367, 1.874581996877085, 1.8726698260600845, 1.8701104559272181, 1.8723480003109678, 1.88482657304381, 1.912990287958233, 1.9622832588867158, 2.0381495996617387, 2.146033424115786, 2.2913788460813382, 2.4796299793908716, 2.716230937876878, 3.006625835371832]
	Cd_min = 0.0037
	Cl @ Cd_min = 0.7
	k-factor (drag polar) = 0.006
	Cl for Cd curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cd curve (deg) = [0.08584, 0.08049322782174093, 0.07532638067471886, 0.07033945855893374, 0.06553246147438566, 0.06090538942107452, 0.0564582423990004, 0.05219102040816323, 0.04810372344856307, 0.044196351520199885, 0.04046890462307368, 0.036921382757184484, 0.03355378592253226, 0.030366114119117014, 0.027358367346938764, 0.02453054560599749, 0.021882648896293204, 0.0194146772178259, 0.017126630570595575, 0.015018508954602239, 0.01309031236984589, 0.011342040816326525, 0.009773694294044141, 0.008385272802998743, 0.007176776343190331, 0.006148204914618905, 0.005299558517284461, 0.004630837151187003, 0.0041420408163265286, 0.0038331695127030393, 0.003704223240316535, 0.003755201999167015, 0.00398610578925448, 0.0043969346105789285, 0.004987688463140362, 0.00575836734693878, 0.006708971261974182, 0.007839500208246569, 0.00914995418575594, 0.010640333194502295, 0.012310637234485633, 0.014160866305705962, 0.016191020408163274, 0.01840109954185757, 0.020791103706788855, 0.023361032902957116, 0.026110887130362373, 0.029040666389004613, 0.03215037067888383, 0.03544]
	Cm_alpha = 0.0 1/deg
	Cm_ac = -0.18
	Cm_ac @ stall = -0.07
	Cl for Cm curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cm curve (deg) = [-0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07, -0.07000000000000002, -0.07000000000000002, -0.07000000000000002, -0.07000000000000002, -0.07000000000000003, -0.07000000000000003]
	x_ac/c = 0.26
	M_cr = 0.72	Transition point upper side = 0.6
	Transition point lower side = 0.53

	.....................................
	                            panel tip
	c_t = 4.119248842650833 m
	epsilon_t = 0.0 deg
	-------------------------------------
	Airfoil
	-------------------------------------
	Name: NACA66_209
	Type: LAMINAR
	t/c = 0.14
	r_le/c = 0.01
	x coordinates = [1.0, 0.994006, 0.983386, 0.970838, 0.956749, 0.941664, 0.926069, 0.910206, 0.894206, 0.878188, 0.862181, 0.846135, 0.830169, 0.814353, 0.798675, 0.783203, 0.767887, 0.75264, 0.737487, 0.722361, 0.707239, 0.692153, 0.677029, 0.661927, 0.646819, 0.631622, 0.61641, 0.601129, 0.585763, 0.570377, 0.554889, 0.539335, 0.523758, 0.508071, 0.492338, 0.476598, 0.460783, 0.444983, 0.4292, 0.41334, 0.397526, 0.381718, 0.365856, 0.350067, 0.334254, 0.318437, 0.302698, 0.286939, 0.271235, 0.255626, 0.240016, 0.224544, 0.209135, 0.193824, 0.178699, 0.163656, 0.148894, 0.134303, 0.120093, 0.106264, 0.093014, 0.080466, 0.068817, 0.058277, 0.048968, 0.04095, 0.034107, 0.028318, 0.023422, 0.019268, 0.015742, 0.012736, 0.010163, 0.007973, 0.006131, 0.004588, 0.003305, 0.002258, 0.001429, 8.04E-4, 3.67E-4, 1.34E-4, 1.24E-4, 3.85E-4, 0.001067, 0.002323, 0.004054, 0.006076, 0.008322, 0.010813, 0.013638, 0.016901, 0.020701, 0.025156, 0.030445, 0.03683, 0.044552, 0.053784, 0.064671, 0.076984, 0.090477, 0.104731, 0.119555, 0.134719, 0.150121, 0.165678, 0.181294, 0.197029, 0.212727, 0.228544, 0.244373, 0.260305, 0.276313, 0.292258, 0.308313, 0.324361, 0.34039, 0.356505, 0.372578, 0.388641, 0.40479, 0.420893, 0.437035, 0.453272, 0.469419, 0.485522, 0.50161, 0.517623, 0.533645, 0.549641, 0.56555, 0.581512, 0.597505, 0.613415, 0.629357, 0.645398, 0.66153, 0.67775, 0.693923, 0.710115, 0.726467, 0.742884, 0.759307, 0.775785, 0.792255, 0.808645, 0.824889, 0.841141, 0.857372, 0.873509, 0.889399, 0.904773, 0.919496, 0.933608, 0.94713, 0.960087, 0.972396, 0.983792, 0.993971, 1.0]
	z coordinates = [-0.003551, -0.002179, 3.36E-4, 0.00337, 0.006834, 0.01058, 0.014491, 0.018507, 0.02258, 0.026678, 0.030812, 0.034976, 0.039128, 0.043224, 0.04722, 0.05107, 0.054741, 0.058241, 0.061558, 0.064679, 0.067625, 0.070369, 0.072928, 0.075295, 0.077451, 0.079424, 0.08121, 0.082806, 0.084234, 0.085486, 0.086567, 0.087501, 0.088274, 0.088896, 0.089393, 0.089745, 0.089969, 0.090072, 0.090032, 0.089867, 0.089585, 0.089164, 0.08862, 0.087959, 0.087155, 0.086239, 0.085195, 0.08401, 0.082716, 0.081272, 0.079693, 0.077978, 0.076102, 0.074082, 0.071897, 0.069537, 0.067014, 0.064293, 0.061408, 0.058329, 0.055095, 0.051707, 0.04825, 0.044773, 0.041397, 0.038155, 0.035079, 0.032155, 0.029325, 0.02656, 0.023842, 0.021184, 0.018614, 0.016132, 0.013724, 0.011397, 0.009156, 0.006998, 0.00492, 0.00292, 9.99E-4, -8.45E-4, -0.002625, -0.004408, -0.006138, -0.00762, -0.008786, -0.009835, -0.010945, -0.012144, -0.013347, -0.014503, -0.015682, -0.016979, -0.018414, -0.020007, -0.02184, -0.023856, -0.026013, -0.028252, -0.030466, -0.032594, -0.034597, -0.036481, -0.038218, -0.039846, -0.04132, -0.042688, -0.043908, -0.045006, -0.04598, -0.046836, -0.047605, -0.048264, -0.048812, -0.049282, -0.049637, -0.049901, -0.050085, -0.050153, -0.050139, -0.050038, -0.049835, -0.049562, -0.049224, -0.048791, -0.04827, -0.047653, -0.046925, -0.046111, -0.045183, -0.044129, -0.042985, -0.041738, -0.040364, -0.038878, -0.037299, -0.035652, -0.03395, -0.032155, -0.030283, -0.028382, -0.026443, -0.024472, -0.022487, -0.020493, -0.018462, -0.016363, -0.014223, -0.012053, -0.009906, -0.007901, -0.006158, -0.004753, -0.003726, -0.003105, -0.002855, -0.002918, -0.003229, -0.003551]
	alpha_0l = -3.0 deg
	alpha_star = 10.0 deg
	alpha_stall = 17.0 deg
	Cl_alpha = 6.245699999999999 1/rad
	Cl0 = 0.37
	Cl_star = 1.2
	Cl_max = 1.55
	Alpha for Cl curve (deg) = [-30.0 deg, -28.775510204081634 deg, -27.551020408163268 deg, -26.326530612244902 deg, -25.102040816326536 deg, -23.87755102040817 deg, -22.653061224489804 deg, -21.428571428571438 deg, -20.20408163265307 deg, -18.979591836734706 deg, -17.75510204081634 deg, -16.530612244897974 deg, -15.306122448979604 deg, -14.081632653061238 deg, -12.857142857142868 deg, -11.632653061224502 deg, -10.408163265306133 deg, -9.183673469387766 deg, -7.9591836734693988 deg, -6.734693877551031 deg, -5.510204081632663 deg, -4.285714285714295 deg, -3.0612244897959275 deg, -1.8367346938775606 deg, -0.6122448979591932 deg, 0.6122448979591741 deg, 1.8367346938775415 deg, 3.0612244897959089 deg, 4.2857142857142758 deg, 5.5102040816326436 deg, 6.7346938775510115 deg, 7.959183673469379 deg, 9.183673469387745 deg, 10.408163265306115 deg, 11.632653061224481 deg, 12.85714285714285 deg, 14.081632653061217 deg, 15.306122448979586 deg, 16.530612244897952 deg, 17.755102040816318 deg, 18.979591836734684 deg, 20.20408163265305 deg, 21.428571428571416 deg, 22.653061224489782 deg, 23.877551020408148 deg, 25.102040816326515 deg, 26.32653061224488 deg, 27.551020408163247 deg, 28.775510204081613 deg, 30.0 deg]
	Cl curve (deg) = [-2.9002408727542948, -2.766761653458201, -2.633282434162108, -2.4998032148660143, -2.3663239955699207, -2.232844776273827, -2.0993655569777334, -1.9658863376816402, -1.8324071183855466, -1.698927899089453, -1.5654486797933598, -1.4319694604972661, -1.298490241201172, -1.1650110219050789, -1.0315318026089848, -0.8980525833128913, -0.7645733640167972, -0.6310941447207038, -0.49761492542461006, -0.3641357061285163, -0.23065648683242257, -0.09717726753632888, 0.036301951759764806, 0.16978117105585844, 0.3032603903519521, 0.4367396096480458, 0.5702188289441394, 0.7036980482402331, 0.8371772675363267, 0.9706564868324205, 1.1041357061285142, 1.2376149254246078, 1.3710941447207015, 1.5004174545899738, 1.5771078522463982, 1.6018848867410544, 1.5934791997729758, 1.5706214330411883, 1.5520422282447286, 1.5564722270826352, 1.6026420712539342, 1.7092824024576623, 1.8951238623928561, 2.178897092758542, 2.579332735253756, 3.1151614315775427, 3.805113823428917, 4.667920552506926, 5.722312260510593, 6.987019589138976]
	Cd_min = 0.0037
	Cl @ Cd_min = 0.5
	k-factor (drag polar) = 0.006
	Cl for Cd curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cd curve (deg) = [0.07719999999999999, 0.07214710537276134, 0.06727413577675967, 0.06258109121199498, 0.05806797167846729, 0.05373477717617657, 0.04958150770512284, 0.04560816326530609, 0.04181474385672634, 0.038201249479383574, 0.03476768013327778, 0.03151403581840897, 0.028440316534777153, 0.025546522282382328, 0.022832653061224478, 0.02029870887130361, 0.017944689712619734, 0.01577059558517284, 0.013776426488962925, 0.01196218242399, 0.010327863390254054, 0.008873469387755097, 0.007599000416493123, 0.0065044564764681345, 0.005589837567680129, 0.00485514369012911, 0.004300374843815075, 0.0039255310287380244, 0.003730612244897959, 0.0037156184922948776, 0.0038805497709287814, 0.004225406080799669, 0.004750187421907542, 0.0054548937942524, 0.006339525197834241, 0.007404081632653067, 0.008648563098708876, 0.010072969596001671, 0.01167730112453145, 0.013461557684298213, 0.015425739275301959, 0.017569845897542694, 0.019893877551020414, 0.022397834235735124, 0.02508171595168681, 0.027945522698875493, 0.03098925447730115, 0.0342129112869638, 0.03761649312786343, 0.0412]
	Cm_alpha = 0.0 1/deg
	Cm_ac = -0.08
	Cm_ac @ stall = -0.05
	Cl for Cm curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cm curve (deg) = [-0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.05, -0.049999999999999996, -0.04999999999999999, -0.04999999999999998, -0.04999999999999997, -0.04999999999999995, -0.049999999999999926, -0.049999999999999906, -0.04999999999999987, -0.049999999999999836, -0.049999999999999795, -0.049999999999999746]
	x_ac/c = 0.25
	M_cr = 0.76	Transition point upper side = 0.6
	Transition point lower side = 0.6

	.....................................
	                   panel derived data
	S = 48.96405786573109 m²
	S_wet = 97.92811573146218 m²
	lambda = 0.9999999999999999
	AR = 6.0213344693734445
	c_MAC = 4.1192488426508316 m
	X_LE_MAC = 0.7569093270254401 m
	Y_LE_MAC = 4.2926461054584566 m
	Z_LE_MAC = 0.41333480774346565 m
	-------------------------------------
	Symmetric flap
	-------------------------------------
	ID: 'Inner flap'
	Flap type = FOWLER
	Inner station spanwise position = 0.1
	Outer station spanwise position = 0.3
	Inner chord ratio = 0.32
	Outer chord ratio = 0.32
	Mean chord ratio = 0.32
	Minimum deflection = 0.0
	Maximum deflection = 40.0
	.....................................
	-------------------------------------
	Symmetric flap
	-------------------------------------
	ID: 'Outer flap'
	Flap type = FOWLER
	Inner station spanwise position = 0.31
	Outer station spanwise position = 0.78
	Inner chord ratio = 0.32
	Outer chord ratio = 0.32
	Mean chord ratio = 0.32
	Minimum deflection = 0.0
	Maximum deflection = 40.0
	.....................................
	-------------------------------------
	Asymmetric flap
	-------------------------------------
	ID: 'Left aileron'
	Type = PLAIN
	Inner station spanwise position = 0.78
	Outer station spanwise position = 0.95
	Inner chord ratio = 0.32
	Outer chord ratio = 0.32
	Mean chord ratio = 0.32
	Minimum deflection = -25.0
	Maximum deflection = 25.0
	.....................................
	-------------------------------------
	Asymmetric flap
	-------------------------------------
	ID: 'Right aileron'
	Type = PLAIN
	Inner station spanwise position = 0.78
	Outer station spanwise position = 0.95
	Inner chord ratio = 0.32
	Outer chord ratio = 0.32
	Mean chord ratio = 0.32
	Minimum deflection = -25.0
	Maximum deflection = 25.0
	.....................................
	=====================================================
	Spanwise discretized WING, size 29
	........................................................................................................................
	Y(m),	chord(m),		Xle(m),	Zle(m),	twist(deg)
	........................................................................................................................
	0,000	4,253	0,000	0,000	0,000
	0,592	4,145	0,104	0,057	0,000
	1,184	4,038	0,209	0,114	0,000
	1,776	3,930	0,313	0,171	0,000
	2,368	3,822	0,418	0,228	0,000
	2,960	3,715	0,522	0,285	0,000
	3,553	3,607	0,626	0,342	0,000
	4,145	3,499	0,731	0,399	0,000
	4,737	3,392	0,835	0,456	0,000
	5,151	3,316	0,908	0,496	0,000
	6,513	3,117	1,148	0,627	-0,226
	7,105	3,032	1,253	0,684	-0,324
	7,697	2,948	1,357	0,741	-0,422
	8,289	2,863	1,462	0,798	-0,520
	8,881	2,778	1,566	0,855	-0,618
	9,473	2,693	1,670	0,912	-0,716
	10,066	2,609	1,775	0,969	-0,814
	10,658	2,524	1,879	1,026	-0,912
	11,250	2,439	1,984	1,083	-1,010
	11,842	2,355	2,088	1,140	-1,108
	12,434	2,270	2,192	1,197	-1,206
	13,026	2,185	2,297	1,254	-1,304
	13,618	2,100	2,401	1,311	-1,402
	14,210	2,016	2,506	1,368	-1,500
	14,802	1,931	2,610	1,425	-1,599
	15,394	1,846	2,714	1,482	-1,697
	15,986	1,761	2,819	1,539	-1,795
	16,578	1,677	2,923	1,596	-1,893
	17,171	1,592	3,028	1,653	-1,991
	=====================================
	Overall wing derived data
	Span: 34.34116884366766 m
	Semi-span: 17.17058442183383 m
	Surface of planform: 98.26703999999995 m²
	Surface wetted: 196.5340799999999 m²
	Aspect-ratio: 12.00113362068595
	Mean aerodynamic chord: 3.0400423940491539 m
	(X,Y,Z)_LE of mean aerodynamic chord: [1.2788293051835877 m, 7.2526013888820327 m, 0.6983460846915974 m]
	Symmetric Flaps Control surface area: 21.453600411489369 m²
	Slats Control surface area: 0.0 m²
	Asymmetric Flaps Control surface area: 0.0 m²
	Spoilers Control surface area: 0.0 m²
	Total Control surface area: 21.45360041148936 m²
	Transition point upper surface: 0.6
	Transition point lower surface: 0.5533333333333333
[email protected]	-------------------------------------
	Lifting surface
	-------------------------------------
	ID: 'IRON Horizontal Tail'
	Type: HORIZONTAL_TAIL
	-------------------------------------
	No. panels = 1
	Main spar position referred to chord = 0.25
	Secondary spar position referred to chord = 0.55
	Surface roughness = 0.00000405 m
	-------------------------------------
	Lifting surface panel
	-------------------------------------
	ID: 'Horizontal tail panel'
	Span = 6.5 m
	Lambda_LE = 10.0 deg
	Lambda_c/4 = 9.999999999999994 deg
	Lambda_c/2 = 9.9999999999999929 deg
	Lambda_TE = 9.999999999999985 deg
	Lambda_TE = 9.999999999999985 deg
	.....................................
	                           panel root
	c_r = 3.6399999999999997 m
	epsilon_r = 0.0 deg
	-------------------------------------
	Airfoil
	-------------------------------------
	Name: NACA0014
	Type: CONVENTIONAL
	t/c = 0.14
	r_le/c = 0.0247
	x coordinates = [1.0, 0.993022, 0.981305, 0.968038, 0.9533, 0.937304, 0.920338, 0.902687, 0.884583, 0.866193, 0.847624, 0.828946, 0.8102, 0.791413, 0.772599, 0.753771, 0.734935, 0.716098, 0.697264, 0.678438, 0.659623, 0.640824, 0.622043, 0.603286, 0.584555, 0.565855, 0.547191, 0.528566, 0.509986, 0.491454, 0.472977, 0.454559, 0.436208, 0.417929, 0.399729, 0.381616, 0.3636, 0.34569, 0.327899, 0.310238, 0.292725, 0.27538, 0.258224, 0.241288, 0.224609, 0.208231, 0.192213, 0.176624, 0.161548, 0.14708, 0.133319, 0.120362, 0.108288, 0.097147, 0.086956, 0.077695, 0.069319, 0.06176, 0.054945, 0.048796, 0.043239, 0.038209, 0.033647, 0.029501, 0.025726, 0.022286, 0.01915, 0.016294, 0.013698, 0.011347, 0.009229, 0.007337, 0.005666, 0.004214, 0.00298, 0.001965, 0.001166, 5.82E-4, 2.03E-4, 2.2E-5, 2.2E-5, 2.03E-4, 5.82E-4, 0.001166, 0.001965, 0.00298, 0.004214, 0.005666, 0.007337, 0.009229, 0.011347, 0.013698, 0.016294, 0.01915, 0.022286, 0.025726, 0.029501, 0.033647, 0.038209, 0.043239, 0.048796, 0.054945, 0.061761, 0.069319, 0.077695, 0.086956, 0.097147, 0.108288, 0.120362, 0.13332, 0.147081, 0.161549, 0.176625, 0.192214, 0.208232, 0.224609, 0.241289, 0.258224, 0.27538, 0.292726, 0.310239, 0.327899, 0.345691, 0.363601, 0.381617, 0.399729, 0.417929, 0.436208, 0.45456, 0.472977, 0.491454, 0.509986, 0.528566, 0.547191, 0.565855, 0.584555, 0.603286, 0.622043, 0.640824, 0.659623, 0.678438, 0.697265, 0.716098, 0.734936, 0.753771, 0.7726, 0.791413, 0.810201, 0.828947, 0.847625, 0.866193, 0.884583, 0.902687, 0.920338, 0.937304, 0.9533, 0.968038, 0.981305, 0.993022, 1.0]
	z coordinates = [0.001575, 0.002794, 0.004816, 0.007072, 0.009536, 0.012162, 0.014893, 0.017678, 0.020475, 0.023256, 0.026005, 0.028711, 0.031368, 0.033972, 0.03652, 0.039012, 0.041445, 0.043819, 0.046131, 0.04838, 0.050564, 0.052681, 0.054729, 0.056704, 0.058603, 0.060424, 0.062162, 0.063813, 0.065374, 0.066839, 0.068204, 0.069464, 0.070612, 0.071643, 0.07255, 0.073328, 0.073968, 0.074464, 0.074808, 0.074991, 0.075007, 0.074847, 0.074501, 0.073963, 0.073226, 0.072282, 0.071129, 0.069766, 0.068199, 0.066437, 0.064501, 0.062415, 0.060211, 0.057924, 0.055588, 0.053231, 0.050878, 0.048545, 0.046242, 0.043974, 0.041741, 0.039543, 0.037375, 0.035234, 0.033114, 0.031007, 0.02891, 0.026815, 0.024718, 0.022614, 0.020497, 0.018366, 0.016217, 0.014052, 0.011872, 0.009683, 0.007494, 0.005315, 0.003157, 0.00104, -0.00104, -0.003157, -0.005315, -0.007494, -0.009683, -0.011872, -0.014052, -0.016217, -0.018366, -0.020497, -0.022614, -0.024718, -0.026815, -0.02891, -0.031007, -0.033114, -0.035234, -0.037375, -0.039543, -0.041741, -0.043974, -0.046242, -0.048545, -0.050878, -0.053231, -0.055588, -0.057924, -0.060211, -0.062415, -0.064501, -0.066437, -0.068199, -0.069766, -0.071129, -0.072282, -0.073226, -0.073963, -0.074501, -0.074847, -0.075007, -0.074991, -0.074808, -0.074464, -0.073968, -0.073328, -0.07255, -0.071643, -0.070612, -0.069464, -0.068204, -0.066839, -0.065374, -0.063813, -0.062162, -0.060424, -0.058603, -0.056704, -0.054729, -0.052681, -0.050564, -0.04838, -0.046131, -0.043819, -0.041445, -0.039012, -0.03652, -0.033972, -0.031368, -0.028711, -0.026005, -0.023256, -0.020475, -0.017678, -0.014893, -0.012162, -0.009536, -0.007072, -0.004816, -0.002794, -0.001575]
	alpha_0l = 0.0 deg
	alpha_star = 10.0 deg
	alpha_stall = 19.0 deg
	Cl_alpha = 0.10999999999999999 1/deg
	Cl0 = 0.0
	Cl_star = 1.2
	Cl_max = 2.0
	Alpha for Cl curve (deg) = [-30.0 deg, -28.775510204081634 deg, -27.551020408163268 deg, -26.326530612244902 deg, -25.102040816326536 deg, -23.87755102040817 deg, -22.653061224489804 deg, -21.428571428571438 deg, -20.20408163265307 deg, -18.979591836734706 deg, -17.75510204081634 deg, -16.530612244897974 deg, -15.306122448979604 deg, -14.081632653061238 deg, -12.857142857142868 deg, -11.632653061224502 deg, -10.408163265306133 deg, -9.183673469387766 deg, -7.9591836734693988 deg, -6.734693877551031 deg, -5.510204081632663 deg, -4.285714285714295 deg, -3.0612244897959275 deg, -1.8367346938775606 deg, -0.6122448979591932 deg, 0.6122448979591741 deg, 1.8367346938775415 deg, 3.0612244897959089 deg, 4.2857142857142758 deg, 5.5102040816326436 deg, 6.7346938775510115 deg, 7.959183673469379 deg, 9.183673469387745 deg, 10.408163265306115 deg, 11.632653061224481 deg, 12.85714285714285 deg, 14.081632653061217 deg, 15.306122448979586 deg, 16.530612244897952 deg, 17.755102040816318 deg, 18.979591836734684 deg, 20.20408163265305 deg, 21.428571428571416 deg, 22.653061224489782 deg, 23.877551020408148 deg, 25.102040816326515 deg, 26.32653061224488 deg, 27.551020408163247 deg, 28.775510204081613 deg, 30.0 deg]
	Cl curve (deg) = [-3.3, -3.165306122448979, -3.030612244897959, -2.8959183673469386, -2.7612244897959184, -2.626530612244898, -2.491836734693878, -2.3571428571428577, -2.2224489795918374, -2.087755102040817, -1.9530612244897971, -1.8183673469387769, -1.6836734693877562, -1.548979591836736, -1.4142857142857153, -1.279591836734695, -1.1448979591836745, -1.0102040816326543, -0.8755102040816337, -0.7408163265306134, -0.6061224489795929, -0.4714285714285724, -0.336734693877552, -0.20204081632653165, -0.06734693877551125, 0.06734693877550915, 0.20204081632652954, 0.33673469387754995, 0.4714285714285703, 0.6061224489795908, 0.7408163265306111, 0.8755102040816316, 1.0102040816326519, 1.1463032693293873, 1.2984501922384921, 1.460932944606411, 1.6215117283898128, 1.767946745545363, 1.8879981980297305, 1.969426287799584, 1.9999912168115892, 1.9674531870224148, 1.8595724003887306, 1.6641090588672012, 1.3688233644144963, 0.9614755189872821, 0.429825724542225, -0.23836581696400527, -1.055338903574739, -2.0333333333333257]
	Cd_min = 0.0072
	Cl @ Cd_min = 0.0
	k-factor (drag polar) = 0.0018
	Cl for Cd curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cd curve (deg) = [0.023399999999999997, 0.022104539775093707, 0.020863057059558515, 0.019675551853394414, 0.01854202415660141, 0.017462473969179503, 0.016436901291128687, 0.015465306122448973, 0.01454768846314035, 0.013684048313202826, 0.012874385672636395, 0.012118700541441062, 0.011416992919616821, 0.010769262807163678, 0.010175510204081629, 0.009635735110370677, 0.009149937526030818, 0.008718117451062057, 0.008340274885464388, 0.008016409829237816, 0.007746522282382339, 0.007530612244897959, 0.007368679716784672, 0.007260724698042482, 0.007206747188671387, 0.007206747188671387, 0.007260724698042483, 0.007368679716784674, 0.00753061224489796, 0.007746522282382342, 0.00801640982923782, 0.008340274885464391, 0.00871811745106206, 0.009149937526030823, 0.00963573511037068, 0.010175510204081636, 0.010769262807163683, 0.011416992919616828, 0.012118700541441067, 0.012874385672636404, 0.013684048313202832, 0.014547688463140359, 0.015465306122448981, 0.0164369012911287, 0.017462473969179514, 0.018542024156601424, 0.019675551853394427, 0.02086305705955853, 0.022104539775093725, 0.023399999999999997]
	Cm_alpha = 0.0 1/deg
	Cm_ac = 0.0
	Cm_ac @ stall = -0.09
	Cl for Cm curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cm curve (deg) = [-0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09000000000000001, -0.09000000000000001, -0.09000000000000001, -0.09000000000000001]
	x_ac/c = 0.25
	M_cr = 0.68	Transition point upper side = 0.12
	Transition point lower side = 0.12

	.....................................
	                            panel tip
	c_t = 3.6399999999999997 m
	epsilon_t = 0.0 deg
	-------------------------------------
	Airfoil
	-------------------------------------
	Name: NACA0014
	Type: CONVENTIONAL
	t/c = 0.14
	r_le/c = 0.0247
	x coordinates = [1.0, 0.993022, 0.981305, 0.968038, 0.9533, 0.937304, 0.920338, 0.902687, 0.884583, 0.866193, 0.847624, 0.828946, 0.8102, 0.791413, 0.772599, 0.753771, 0.734935, 0.716098, 0.697264, 0.678438, 0.659623, 0.640824, 0.622043, 0.603286, 0.584555, 0.565855, 0.547191, 0.528566, 0.509986, 0.491454, 0.472977, 0.454559, 0.436208, 0.417929, 0.399729, 0.381616, 0.3636, 0.34569, 0.327899, 0.310238, 0.292725, 0.27538, 0.258224, 0.241288, 0.224609, 0.208231, 0.192213, 0.176624, 0.161548, 0.14708, 0.133319, 0.120362, 0.108288, 0.097147, 0.086956, 0.077695, 0.069319, 0.06176, 0.054945, 0.048796, 0.043239, 0.038209, 0.033647, 0.029501, 0.025726, 0.022286, 0.01915, 0.016294, 0.013698, 0.011347, 0.009229, 0.007337, 0.005666, 0.004214, 0.00298, 0.001965, 0.001166, 5.82E-4, 2.03E-4, 2.2E-5, 2.2E-5, 2.03E-4, 5.82E-4, 0.001166, 0.001965, 0.00298, 0.004214, 0.005666, 0.007337, 0.009229, 0.011347, 0.013698, 0.016294, 0.01915, 0.022286, 0.025726, 0.029501, 0.033647, 0.038209, 0.043239, 0.048796, 0.054945, 0.061761, 0.069319, 0.077695, 0.086956, 0.097147, 0.108288, 0.120362, 0.13332, 0.147081, 0.161549, 0.176625, 0.192214, 0.208232, 0.224609, 0.241289, 0.258224, 0.27538, 0.292726, 0.310239, 0.327899, 0.345691, 0.363601, 0.381617, 0.399729, 0.417929, 0.436208, 0.45456, 0.472977, 0.491454, 0.509986, 0.528566, 0.547191, 0.565855, 0.584555, 0.603286, 0.622043, 0.640824, 0.659623, 0.678438, 0.697265, 0.716098, 0.734936, 0.753771, 0.7726, 0.791413, 0.810201, 0.828947, 0.847625, 0.866193, 0.884583, 0.902687, 0.920338, 0.937304, 0.9533, 0.968038, 0.981305, 0.993022, 1.0]
	z coordinates = [0.001575, 0.002794, 0.004816, 0.007072, 0.009536, 0.012162, 0.014893, 0.017678, 0.020475, 0.023256, 0.026005, 0.028711, 0.031368, 0.033972, 0.03652, 0.039012, 0.041445, 0.043819, 0.046131, 0.04838, 0.050564, 0.052681, 0.054729, 0.056704, 0.058603, 0.060424, 0.062162, 0.063813, 0.065374, 0.066839, 0.068204, 0.069464, 0.070612, 0.071643, 0.07255, 0.073328, 0.073968, 0.074464, 0.074808, 0.074991, 0.075007, 0.074847, 0.074501, 0.073963, 0.073226, 0.072282, 0.071129, 0.069766, 0.068199, 0.066437, 0.064501, 0.062415, 0.060211, 0.057924, 0.055588, 0.053231, 0.050878, 0.048545, 0.046242, 0.043974, 0.041741, 0.039543, 0.037375, 0.035234, 0.033114, 0.031007, 0.02891, 0.026815, 0.024718, 0.022614, 0.020497, 0.018366, 0.016217, 0.014052, 0.011872, 0.009683, 0.007494, 0.005315, 0.003157, 0.00104, -0.00104, -0.003157, -0.005315, -0.007494, -0.009683, -0.011872, -0.014052, -0.016217, -0.018366, -0.020497, -0.022614, -0.024718, -0.026815, -0.02891, -0.031007, -0.033114, -0.035234, -0.037375, -0.039543, -0.041741, -0.043974, -0.046242, -0.048545, -0.050878, -0.053231, -0.055588, -0.057924, -0.060211, -0.062415, -0.064501, -0.066437, -0.068199, -0.069766, -0.071129, -0.072282, -0.073226, -0.073963, -0.074501, -0.074847, -0.075007, -0.074991, -0.074808, -0.074464, -0.073968, -0.073328, -0.07255, -0.071643, -0.070612, -0.069464, -0.068204, -0.066839, -0.065374, -0.063813, -0.062162, -0.060424, -0.058603, -0.056704, -0.054729, -0.052681, -0.050564, -0.04838, -0.046131, -0.043819, -0.041445, -0.039012, -0.03652, -0.033972, -0.031368, -0.028711, -0.026005, -0.023256, -0.020475, -0.017678, -0.014893, -0.012162, -0.009536, -0.007072, -0.004816, -0.002794, -0.001575]
	alpha_0l = 0.0 deg
	alpha_star = 10.0 deg
	alpha_stall = 19.0 deg
	Cl_alpha = 0.10999999999999999 1/deg
	Cl0 = 0.0
	Cl_star = 1.2
	Cl_max = 2.0
	Alpha for Cl curve (deg) = [-30.0 deg, -28.775510204081634 deg, -27.551020408163268 deg, -26.326530612244902 deg, -25.102040816326536 deg, -23.87755102040817 deg, -22.653061224489804 deg, -21.428571428571438 deg, -20.20408163265307 deg, -18.979591836734706 deg, -17.75510204081634 deg, -16.530612244897974 deg, -15.306122448979604 deg, -14.081632653061238 deg, -12.857142857142868 deg, -11.632653061224502 deg, -10.408163265306133 deg, -9.183673469387766 deg, -7.9591836734693988 deg, -6.734693877551031 deg, -5.510204081632663 deg, -4.285714285714295 deg, -3.0612244897959275 deg, -1.8367346938775606 deg, -0.6122448979591932 deg, 0.6122448979591741 deg, 1.8367346938775415 deg, 3.0612244897959089 deg, 4.2857142857142758 deg, 5.5102040816326436 deg, 6.7346938775510115 deg, 7.959183673469379 deg, 9.183673469387745 deg, 10.408163265306115 deg, 11.632653061224481 deg, 12.85714285714285 deg, 14.081632653061217 deg, 15.306122448979586 deg, 16.530612244897952 deg, 17.755102040816318 deg, 18.979591836734684 deg, 20.20408163265305 deg, 21.428571428571416 deg, 22.653061224489782 deg, 23.877551020408148 deg, 25.102040816326515 deg, 26.32653061224488 deg, 27.551020408163247 deg, 28.775510204081613 deg, 30.0 deg]
	Cl curve (deg) = [-3.3, -3.165306122448979, -3.030612244897959, -2.8959183673469386, -2.7612244897959184, -2.626530612244898, -2.491836734693878, -2.3571428571428577, -2.2224489795918374, -2.087755102040817, -1.9530612244897971, -1.8183673469387769, -1.6836734693877562, -1.548979591836736, -1.4142857142857153, -1.279591836734695, -1.1448979591836745, -1.0102040816326543, -0.8755102040816337, -0.7408163265306134, -0.6061224489795929, -0.4714285714285724, -0.336734693877552, -0.20204081632653165, -0.06734693877551125, 0.06734693877550915, 0.20204081632652954, 0.33673469387754995, 0.4714285714285703, 0.6061224489795908, 0.7408163265306111, 0.8755102040816316, 1.0102040816326519, 1.1463032693293873, 1.2984501922384921, 1.460932944606411, 1.6215117283898128, 1.767946745545363, 1.8879981980297305, 1.969426287799584, 1.9999912168115892, 1.9674531870224148, 1.8595724003887306, 1.6641090588672012, 1.3688233644144963, 0.9614755189872821, 0.429825724542225, -0.23836581696400527, -1.055338903574739, -2.0333333333333257]
	Cd_min = 0.0072
	Cl @ Cd_min = 0.0
	k-factor (drag polar) = 0.0018
	Cl for Cd curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cd curve (deg) = [0.023399999999999997, 0.022104539775093707, 0.020863057059558515, 0.019675551853394414, 0.01854202415660141, 0.017462473969179503, 0.016436901291128687, 0.015465306122448973, 0.01454768846314035, 0.013684048313202826, 0.012874385672636395, 0.012118700541441062, 0.011416992919616821, 0.010769262807163678, 0.010175510204081629, 0.009635735110370677, 0.009149937526030818, 0.008718117451062057, 0.008340274885464388, 0.008016409829237816, 0.007746522282382339, 0.007530612244897959, 0.007368679716784672, 0.007260724698042482, 0.007206747188671387, 0.007206747188671387, 0.007260724698042483, 0.007368679716784674, 0.00753061224489796, 0.007746522282382342, 0.00801640982923782, 0.008340274885464391, 0.00871811745106206, 0.009149937526030823, 0.00963573511037068, 0.010175510204081636, 0.010769262807163683, 0.011416992919616828, 0.012118700541441067, 0.012874385672636404, 0.013684048313202832, 0.014547688463140359, 0.015465306122448981, 0.0164369012911287, 0.017462473969179514, 0.018542024156601424, 0.019675551853394427, 0.02086305705955853, 0.022104539775093725, 0.023399999999999997]
	Cm_alpha = 0.0 1/deg
	Cm_ac = 0.0
	Cm_ac @ stall = -0.09
	Cl for Cm curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cm curve (deg) = [-0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09000000000000001, -0.09000000000000001, -0.09000000000000001, -0.09000000000000001]
	x_ac/c = 0.25
	M_cr = 0.68	Transition point upper side = 0.12
	Transition point lower side = 0.12

	.....................................
	                   panel derived data
	S = 19.21399999999999 m²
	S_wet = 38.42799999999998 m²
	lambda = 0.9999999999999998
	AR = 2.1989174560216513
	c_MAC = 3.6399999999999988 m
	X_LE_MAC = 0.28653134365125543 m
	Y_LE_MAC = 1.6249999999999996 m
	Z_LE_MAC = 0.4354174377005741 m
	-------------------------------------
	Symmetric flap
	-------------------------------------
	ID: 'Elevator'
	Flap type = PLAIN
	Inner station spanwise position = 0.0
	Outer station spanwise position = 1.0
	Inner chord ratio = 0.3
	Outer chord ratio = 0.3
	Mean chord ratio = 0.3
	Minimum deflection = -25.0
	Maximum deflection = 5.0
	.....................................
	=====================================================
	Spanwise discretized HORIZONTAL_TAIL, size 30
	........................................................................................................................
	Y(m),	chord(m),		Xle(m),	Zle(m),	twist(deg)
	........................................................................................................................
	0,000	3,640	0,000	0,000	0,000
	0,217	3,594	0,038	0,058	0,000
	0,433	3,549	0,076	0,116	0,000
	0,650	3,503	0,115	0,174	0,000
	0,866	3,458	0,153	0,232	0,000
	1,083	3,412	0,191	0,290	0,000
	1,299	3,367	0,229	0,348	0,000
	1,516	3,321	0,267	0,406	0,000
	1,732	3,275	0,305	0,464	0,000
	1,949	3,230	0,344	0,522	0,000
	2,165	3,184	0,382	0,580	0,000
	2,382	3,139	0,420	0,638	0,000
	2,598	3,093	0,458	0,696	0,000
	2,815	3,048	0,496	0,754	0,000
	3,031	3,002	0,534	0,812	0,000
	3,248	2,957	0,573	0,870	0,000
	3,464	2,911	0,611	0,928	0,000
	3,681	2,865	0,649	0,986	0,000
	3,897	2,820	0,687	1,044	0,000
	4,114	2,774	0,725	1,102	0,000
	4,330	2,729	0,763	1,160	0,000
	4,547	2,683	0,802	1,218	0,000
	4,763	2,638	0,840	1,276	0,000
	4,980	2,592	0,878	1,334	0,000
	5,196	2,546	0,916	1,392	0,000
	5,413	2,501	0,954	1,450	0,000
	5,629	2,455	0,993	1,508	0,000
	5,846	2,410	1,031	1,566	0,000
	6,062	2,364	1,069	1,624	0,000
	6,279	2,319	1,107	1,682	0,000
	=====================================
	Overall wing derived data
	Span: 12.557035741757886 m
	Semi-span: 6.278517870878943 m
	Surface of planform: 38.42799999999998 m²
	Surface wetted: 76.85599999999996 m²
	Aspect-ratio: 4.1032358337614525
	Mean aerodynamic chord: 2.9480258176833836 m
	(X,Y,Z)_LE of mean aerodynamic chord: [0.49905552641967599 m, 2.8302845339636553 m, 0.7583724552258575 m]
	Symmetric Flaps Control surface area: 13.315867070890576 m²
	Slats Control surface area: 0.0 m²
	Asymmetric Flaps Control surface area: 0.0 m²
	Spoilers Control surface area: 0.0 m²
	Total Control surface area: 13.315867070890572 m²
	Transition point upper surface: 0.12
	Transition point lower surface: 0.12
	-------------------------------------
	Lifting surface
	-------------------------------------
	ID: 'IRON Vertical Tail'
	Type: VERTICAL_TAIL
	-------------------------------------
	No. panels = 1
	Main spar position referred to chord = 0.25
	Secondary spar position referred to chord = 0.55
	Surface roughness = 0.00000405 m
	-------------------------------------
	Lifting surface panel
	-------------------------------------
	ID: 'Vertical tail panel'
	Span = 5.779999999999999 m
	Lambda_LE = 45.0 deg
	Lambda_c/4 = 44.999999999999986 deg
	Lambda_c/2 = 44.999999999999979 deg
	Lambda_TE = 44.999999999999979 deg
	Lambda_TE = 44.999999999999979 deg
	.....................................
	                           panel root
	c_r = 5.16 m
	epsilon_r = 0.0 deg
	-------------------------------------
	Airfoil
	-------------------------------------
	Name: NACA0012
	Type: CONVENTIONAL
	t/c = 0.12
	r_le/c = 0.0158
	x coordinates = [1.0, 0.99372, 0.982766, 0.969978, 0.955648, 0.940249, 0.924212, 0.907834, 0.89128, 0.874637, 0.857947, 0.84123, 0.824498, 0.807755, 0.791005, 0.77425, 0.757492, 0.740731, 0.72397, 0.707209, 0.690451, 0.673695, 0.656944, 0.640199, 0.62346, 0.606731, 0.590011, 0.573303, 0.556607, 0.539927, 0.523262, 0.506616, 0.48999, 0.473385, 0.456805, 0.440251, 0.423726, 0.407233, 0.390775, 0.374354, 0.357976, 0.341643, 0.325361, 0.309135, 0.292972, 0.276878, 0.260863, 0.244936, 0.22911, 0.213401, 0.197828, 0.182416, 0.167201, 0.152227, 0.137561, 0.123289, 0.109532, 0.096442, 0.084194, 0.072956, 0.06285, 0.053918, 0.046123, 0.039362, 0.033509, 0.028432, 0.024011, 0.020146, 0.016754, 0.013769, 0.011142, 0.008834, 0.006819, 0.005076, 0.003597, 0.002376, 0.001412, 7.03E-4, 2.45E-4, 2.6E-5, 2.6E-5, 2.45E-4, 7.03E-4, 0.001412, 0.002376, 0.003597, 0.005076, 0.006819, 0.008834, 0.011142, 0.013769, 0.016754, 0.020146, 0.024011, 0.028432, 0.033509, 0.039363, 0.046123, 0.053919, 0.06285, 0.072956, 0.084194, 0.096442, 0.109532, 0.123289, 0.137561, 0.152228, 0.167201, 0.182417, 0.197828, 0.213401, 0.22911, 0.244936, 0.260863, 0.276879, 0.292972, 0.309136, 0.325361, 0.341643, 0.357976, 0.374355, 0.390775, 0.407233, 0.423727, 0.440251, 0.456805, 0.473386, 0.48999, 0.506616, 0.523263, 0.539927, 0.556608, 0.573303, 0.590011, 0.606731, 0.623461, 0.640199, 0.656944, 0.673695, 0.690451, 0.70721, 0.72397, 0.740731, 0.757492, 0.77425, 0.791005, 0.807755, 0.824498, 0.84123, 0.857947, 0.874637, 0.89128, 0.907834, 0.924213, 0.940249, 0.955649, 0.969978, 0.982766, 0.99372, 1.0]
	z coordinates = [0.00126, 0.002138, 0.003653, 0.005396, 0.007317, 0.009346, 0.011419, 0.013497, 0.015557, 0.017589, 0.019588, 0.021551, 0.023478, 0.025368, 0.027222, 0.029039, 0.030819, 0.032562, 0.034267, 0.035934, 0.037562, 0.039149, 0.040696, 0.0422, 0.043661, 0.045077, 0.046446, 0.047766, 0.049036, 0.050253, 0.051414, 0.052518, 0.053561, 0.05454, 0.055453, 0.056295, 0.057063, 0.057753, 0.058361, 0.058882, 0.059311, 0.059644, 0.059875, 0.059998, 0.060007, 0.059894, 0.059654, 0.059277, 0.058757, 0.058084, 0.057248, 0.056241, 0.055054, 0.053676, 0.052101, 0.050328, 0.04836, 0.046216, 0.043928, 0.041542, 0.039116, 0.036701, 0.034339, 0.032051, 0.029846, 0.027721, 0.025669, 0.023677, 0.021733, 0.019823, 0.017936, 0.016059, 0.014185, 0.012303, 0.010409, 0.008502, 0.006586, 0.00467, 0.002769, 9.09E-4, -9.09E-4, -0.002769, -0.00467, -0.006586, -0.008502, -0.010409, -0.012303, -0.014185, -0.016059, -0.017936, -0.019823, -0.021733, -0.023677, -0.025669, -0.027721, -0.029846, -0.032051, -0.034339, -0.036701, -0.039116, -0.041542, -0.043928, -0.046216, -0.04836, -0.050328, -0.052101, -0.053676, -0.055054, -0.056241, -0.057248, -0.058084, -0.058757, -0.059277, -0.059654, -0.059894, -0.060007, -0.059998, -0.059875, -0.059644, -0.059311, -0.058882, -0.058361, -0.057753, -0.057063, -0.056295, -0.055453, -0.05454, -0.053561, -0.052518, -0.051414, -0.050253, -0.049036, -0.047766, -0.046446, -0.045077, -0.043661, -0.0422, -0.040696, -0.039149, -0.037562, -0.035934, -0.034267, -0.032562, -0.030819, -0.029039, -0.027222, -0.025368, -0.023478, -0.021551, -0.019588, -0.017589, -0.015557, -0.013497, -0.011419, -0.009346, -0.007317, -0.005396, -0.003653, -0.002138, -0.00126]
	alpha_0l = 0.0 deg
	alpha_star = 11.0 deg
	alpha_stall = 20.1 deg
	Cl_alpha = 6.9199999999999999 1/rad
	Cl0 = 0.0
	Cl_star = 1.23
	Cl_max = 1.86
	Alpha for Cl curve (deg) = [-30.0 deg, -28.775510204081634 deg, -27.551020408163268 deg, -26.326530612244902 deg, -25.102040816326536 deg, -23.87755102040817 deg, -22.653061224489804 deg, -21.428571428571438 deg, -20.20408163265307 deg, -18.979591836734706 deg, -17.75510204081634 deg, -16.530612244897974 deg, -15.306122448979604 deg, -14.081632653061238 deg, -12.857142857142868 deg, -11.632653061224502 deg, -10.408163265306133 deg, -9.183673469387766 deg, -7.9591836734693988 deg, -6.734693877551031 deg, -5.510204081632663 deg, -4.285714285714295 deg, -3.0612244897959275 deg, -1.8367346938775606 deg, -0.6122448979591932 deg, 0.6122448979591741 deg, 1.8367346938775415 deg, 3.0612244897959089 deg, 4.2857142857142758 deg, 5.5102040816326436 deg, 6.7346938775510115 deg, 7.959183673469379 deg, 9.183673469387745 deg, 10.408163265306115 deg, 11.632653061224481 deg, 12.85714285714285 deg, 14.081632653061217 deg, 15.306122448979586 deg, 16.530612244897952 deg, 17.755102040816318 deg, 18.979591836734684 deg, 20.20408163265305 deg, 21.428571428571416 deg, 22.653061224489782 deg, 23.877551020408148 deg, 25.102040816326515 deg, 26.32653061224488 deg, 27.551020408163247 deg, 28.775510204081613 deg, 30.0 deg]
	Cl curve (deg) = [-3.6233035271402274, -3.475413587256953, -3.3275236473736785, -3.1796337074904044, -3.03174376760713, -2.8838538277238555, -2.735963887840581, -2.5880739479573065, -2.440184008074032, -2.2922940681907575, -2.144404128307483, -1.9965141884242088, -1.8486242485409339, -1.7007343086576594, -1.5528443687743845, -1.4049544288911102, -1.2570644890078353, -1.1091745491245608, -0.9612846092412862, -0.8133946693580115, -0.6655047294747369, -0.5176147895914622, -0.3697248497081876, -0.22183490982491305, -0.07394496994163845, 0.07394496994163614, 0.22183490982491075, 0.3697248497081853, 0.5176147895914599, 0.6655047294747345, 0.8133946693580092, 0.9612846092412838, 1.1091745491245584, 1.257064489007833, 1.4020483393110252, 1.5280050446846811, 1.6328993821658648, 1.717259914880743, 1.7816152059554775, 1.826493818516235, 1.8524243156891775, 1.859935260600471, 1.84955521637628, 1.821812746142769, 1.7772364130260998, 1.7163547801524404, 1.6396964106479528, 1.5477898676388016, 1.441163714251152, 1.3203465136111658]
	Cd_min = 0.0055
	Cl @ Cd_min = 0.0
	k-factor (drag polar) = 0.0035
	Cl for Cd curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cd curve (deg) = [0.037, 0.03448104956268221, 0.032067055393586, 0.029758017492711362, 0.027553935860058297, 0.025454810495626812, 0.0234606413994169, 0.02157142857142856, 0.019787172011661792, 0.018107871720116603, 0.01653352769679299, 0.015064139941690952, 0.013699708454810488, 0.012440233236151597, 0.011285714285714281, 0.010236151603498538, 0.00929154518950437, 0.008451895043731776, 0.007717201166180755, 0.007087463556851309, 0.006562682215743438, 0.006142857142857141, 0.005827988338192419, 0.00561807580174927, 0.005513119533527696, 0.005513119533527696, 0.005618075801749271, 0.00582798833819242, 0.006142857142857144, 0.0065626822157434424, 0.007087463556851315, 0.007717201166180762, 0.008451895043731783, 0.009291545189504377, 0.010236151603498547, 0.011285714285714291, 0.012440233236151607, 0.013699708454810498, 0.015064139941690964, 0.016533527696793004, 0.018107871720116617, 0.01978717201166181, 0.021571428571428575, 0.02346064139941692, 0.025454810495626833, 0.027553935860058325, 0.02975801749271139, 0.03206705539358603, 0.03448104956268224, 0.037]
	Cm_alpha = 0.0 1/deg
	Cm_ac = 0.0
	Cm_ac @ stall = -0.09
	Cl for Cm curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cm curve (deg) = [-0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09000000000000001, -0.09000000000000001, -0.09000000000000001, -0.09000000000000002, -0.09000000000000002, -0.09000000000000004, -0.09000000000000005]
	x_ac/c = 0.25
	M_cr = 0.734	Transition point upper side = 0.12
	Transition point lower side = 0.12

	.....................................
	                            panel tip
	c_t = 5.16 m
	epsilon_t = 0.0 deg
	-------------------------------------
	Airfoil
	-------------------------------------
	Name: NACA0012
	Type: CONVENTIONAL
	t/c = 0.12
	r_le/c = 0.0158
	x coordinates = [1.0, 0.99372, 0.982766, 0.969978, 0.955648, 0.940249, 0.924212, 0.907834, 0.89128, 0.874637, 0.857947, 0.84123, 0.824498, 0.807755, 0.791005, 0.77425, 0.757492, 0.740731, 0.72397, 0.707209, 0.690451, 0.673695, 0.656944, 0.640199, 0.62346, 0.606731, 0.590011, 0.573303, 0.556607, 0.539927, 0.523262, 0.506616, 0.48999, 0.473385, 0.456805, 0.440251, 0.423726, 0.407233, 0.390775, 0.374354, 0.357976, 0.341643, 0.325361, 0.309135, 0.292972, 0.276878, 0.260863, 0.244936, 0.22911, 0.213401, 0.197828, 0.182416, 0.167201, 0.152227, 0.137561, 0.123289, 0.109532, 0.096442, 0.084194, 0.072956, 0.06285, 0.053918, 0.046123, 0.039362, 0.033509, 0.028432, 0.024011, 0.020146, 0.016754, 0.013769, 0.011142, 0.008834, 0.006819, 0.005076, 0.003597, 0.002376, 0.001412, 7.03E-4, 2.45E-4, 2.6E-5, 2.6E-5, 2.45E-4, 7.03E-4, 0.001412, 0.002376, 0.003597, 0.005076, 0.006819, 0.008834, 0.011142, 0.013769, 0.016754, 0.020146, 0.024011, 0.028432, 0.033509, 0.039363, 0.046123, 0.053919, 0.06285, 0.072956, 0.084194, 0.096442, 0.109532, 0.123289, 0.137561, 0.152228, 0.167201, 0.182417, 0.197828, 0.213401, 0.22911, 0.244936, 0.260863, 0.276879, 0.292972, 0.309136, 0.325361, 0.341643, 0.357976, 0.374355, 0.390775, 0.407233, 0.423727, 0.440251, 0.456805, 0.473386, 0.48999, 0.506616, 0.523263, 0.539927, 0.556608, 0.573303, 0.590011, 0.606731, 0.623461, 0.640199, 0.656944, 0.673695, 0.690451, 0.70721, 0.72397, 0.740731, 0.757492, 0.77425, 0.791005, 0.807755, 0.824498, 0.84123, 0.857947, 0.874637, 0.89128, 0.907834, 0.924213, 0.940249, 0.955649, 0.969978, 0.982766, 0.99372, 1.0]
	z coordinates = [0.00126, 0.002138, 0.003653, 0.005396, 0.007317, 0.009346, 0.011419, 0.013497, 0.015557, 0.017589, 0.019588, 0.021551, 0.023478, 0.025368, 0.027222, 0.029039, 0.030819, 0.032562, 0.034267, 0.035934, 0.037562, 0.039149, 0.040696, 0.0422, 0.043661, 0.045077, 0.046446, 0.047766, 0.049036, 0.050253, 0.051414, 0.052518, 0.053561, 0.05454, 0.055453, 0.056295, 0.057063, 0.057753, 0.058361, 0.058882, 0.059311, 0.059644, 0.059875, 0.059998, 0.060007, 0.059894, 0.059654, 0.059277, 0.058757, 0.058084, 0.057248, 0.056241, 0.055054, 0.053676, 0.052101, 0.050328, 0.04836, 0.046216, 0.043928, 0.041542, 0.039116, 0.036701, 0.034339, 0.032051, 0.029846, 0.027721, 0.025669, 0.023677, 0.021733, 0.019823, 0.017936, 0.016059, 0.014185, 0.012303, 0.010409, 0.008502, 0.006586, 0.00467, 0.002769, 9.09E-4, -9.09E-4, -0.002769, -0.00467, -0.006586, -0.008502, -0.010409, -0.012303, -0.014185, -0.016059, -0.017936, -0.019823, -0.021733, -0.023677, -0.025669, -0.027721, -0.029846, -0.032051, -0.034339, -0.036701, -0.039116, -0.041542, -0.043928, -0.046216, -0.04836, -0.050328, -0.052101, -0.053676, -0.055054, -0.056241, -0.057248, -0.058084, -0.058757, -0.059277, -0.059654, -0.059894, -0.060007, -0.059998, -0.059875, -0.059644, -0.059311, -0.058882, -0.058361, -0.057753, -0.057063, -0.056295, -0.055453, -0.05454, -0.053561, -0.052518, -0.051414, -0.050253, -0.049036, -0.047766, -0.046446, -0.045077, -0.043661, -0.0422, -0.040696, -0.039149, -0.037562, -0.035934, -0.034267, -0.032562, -0.030819, -0.029039, -0.027222, -0.025368, -0.023478, -0.021551, -0.019588, -0.017589, -0.015557, -0.013497, -0.011419, -0.009346, -0.007317, -0.005396, -0.003653, -0.002138, -0.00126]
	alpha_0l = 0.0 deg
	alpha_star = 11.0 deg
	alpha_stall = 20.1 deg
	Cl_alpha = 6.9199999999999999 1/rad
	Cl0 = 0.0
	Cl_star = 1.23
	Cl_max = 1.86
	Alpha for Cl curve (deg) = [-30.0 deg, -28.775510204081634 deg, -27.551020408163268 deg, -26.326530612244902 deg, -25.102040816326536 deg, -23.87755102040817 deg, -22.653061224489804 deg, -21.428571428571438 deg, -20.20408163265307 deg, -18.979591836734706 deg, -17.75510204081634 deg, -16.530612244897974 deg, -15.306122448979604 deg, -14.081632653061238 deg, -12.857142857142868 deg, -11.632653061224502 deg, -10.408163265306133 deg, -9.183673469387766 deg, -7.9591836734693988 deg, -6.734693877551031 deg, -5.510204081632663 deg, -4.285714285714295 deg, -3.0612244897959275 deg, -1.8367346938775606 deg, -0.6122448979591932 deg, 0.6122448979591741 deg, 1.8367346938775415 deg, 3.0612244897959089 deg, 4.2857142857142758 deg, 5.5102040816326436 deg, 6.7346938775510115 deg, 7.959183673469379 deg, 9.183673469387745 deg, 10.408163265306115 deg, 11.632653061224481 deg, 12.85714285714285 deg, 14.081632653061217 deg, 15.306122448979586 deg, 16.530612244897952 deg, 17.755102040816318 deg, 18.979591836734684 deg, 20.20408163265305 deg, 21.428571428571416 deg, 22.653061224489782 deg, 23.877551020408148 deg, 25.102040816326515 deg, 26.32653061224488 deg, 27.551020408163247 deg, 28.775510204081613 deg, 30.0 deg]
	Cl curve (deg) = [-3.6233035271402274, -3.475413587256953, -3.3275236473736785, -3.1796337074904044, -3.03174376760713, -2.8838538277238555, -2.735963887840581, -2.5880739479573065, -2.440184008074032, -2.2922940681907575, -2.144404128307483, -1.9965141884242088, -1.8486242485409339, -1.7007343086576594, -1.5528443687743845, -1.4049544288911102, -1.2570644890078353, -1.1091745491245608, -0.9612846092412862, -0.8133946693580115, -0.6655047294747369, -0.5176147895914622, -0.3697248497081876, -0.22183490982491305, -0.07394496994163845, 0.07394496994163614, 0.22183490982491075, 0.3697248497081853, 0.5176147895914599, 0.6655047294747345, 0.8133946693580092, 0.9612846092412838, 1.1091745491245584, 1.257064489007833, 1.4020483393110252, 1.5280050446846811, 1.6328993821658648, 1.717259914880743, 1.7816152059554775, 1.826493818516235, 1.8524243156891775, 1.859935260600471, 1.84955521637628, 1.821812746142769, 1.7772364130260998, 1.7163547801524404, 1.6396964106479528, 1.5477898676388016, 1.441163714251152, 1.3203465136111658]
	Cd_min = 0.0055
	Cl @ Cd_min = 0.0
	k-factor (drag polar) = 0.0035
	Cl for Cd curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cd curve (deg) = [0.037, 0.03448104956268221, 0.032067055393586, 0.029758017492711362, 0.027553935860058297, 0.025454810495626812, 0.0234606413994169, 0.02157142857142856, 0.019787172011661792, 0.018107871720116603, 0.01653352769679299, 0.015064139941690952, 0.013699708454810488, 0.012440233236151597, 0.011285714285714281, 0.010236151603498538, 0.00929154518950437, 0.008451895043731776, 0.007717201166180755, 0.007087463556851309, 0.006562682215743438, 0.006142857142857141, 0.005827988338192419, 0.00561807580174927, 0.005513119533527696, 0.005513119533527696, 0.005618075801749271, 0.00582798833819242, 0.006142857142857144, 0.0065626822157434424, 0.007087463556851315, 0.007717201166180762, 0.008451895043731783, 0.009291545189504377, 0.010236151603498547, 0.011285714285714291, 0.012440233236151607, 0.013699708454810498, 0.015064139941690964, 0.016533527696793004, 0.018107871720116617, 0.01978717201166181, 0.021571428571428575, 0.02346064139941692, 0.025454810495626833, 0.027553935860058325, 0.02975801749271139, 0.03206705539358603, 0.03448104956268224, 0.037]
	Cm_alpha = 0.0 1/deg
	Cm_ac = 0.0
	Cm_ac @ stall = -0.09
	Cl for Cm curve (deg) = [-3.0, -2.877551020408163, -2.7551020408163263, -2.6326530612244894, -2.5102040816326525, -2.3877551020408156, -2.2653061224489788, -2.142857142857142, -2.020408163265305, -1.8979591836734684, -1.7755102040816317, -1.653061224489795, -1.5306122448979584, -1.4081632653061218, -1.2857142857142851, -1.1632653061224485, -1.0408163265306118, -0.9183673469387751, -0.7959183673469383, -0.6734693877551016, -0.5510204081632648, -0.42857142857142805, -0.3061224489795913, -0.18367346938775456, -0.061224489795917825, 0.06122448979591891, 0.18367346938775564, 0.3061224489795924, 0.42857142857142916, 0.5510204081632659, 0.6734693877551027, 0.7959183673469394, 0.9183673469387762, 1.040816326530613, 1.1632653061224496, 1.2857142857142863, 1.408163265306123, 1.5306122448979596, 1.6530612244897962, 1.7755102040816328, 1.8979591836734695, 2.0204081632653064, 2.1428571428571432, 2.26530612244898, 2.387755102040817, 2.510204081632654, 2.6326530612244907, 2.7551020408163276, 2.8775510204081645, 3.0]
	Cm curve (deg) = [-0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09, -0.09000000000000001, -0.09000000000000001, -0.09000000000000001, -0.09000000000000002, -0.09000000000000002, -0.09000000000000004, -0.09000000000000005]
	x_ac/c = 0.25
	M_cr = 0.734	Transition point upper side = 0.12
	Transition point lower side = 0.12

	.....................................
	                   panel derived data
	S = 24.478299999999994 m²
	S_wet = 48.95659999999998 m²
	lambda = 0.9999999999999999
	AR = 1.3648170011806375
	c_MAC = 5.159999999999998 m
	X_LE_MAC = 1.4449999999999992 m
	Y_LE_MAC = 1.4449999999999998 m
	Z_LE_MAC = 0.0 m
	-------------------------------------
	Symmetric flap
	-------------------------------------
	ID: 'Rudder'
	Flap type = PLAIN
	Inner station spanwise position = 0.0
	Outer station spanwise position = 0.9
	Inner chord ratio = 0.35
	Outer chord ratio = 0.35
	Mean chord ratio = 0.35
	Minimum deflection = -25.0
	Maximum deflection = 25.0
	.....................................
	=====================================================
	Spanwise discretized VERTICAL_TAIL, size 30
	........................................................................................................................
	Y(m),	chord(m),		Xle(m),	Zle(m),	twist(deg)
	........................................................................................................................
	0,000	5,160	0,000	0,000	0,000
	0,199	5,096	0,199	0,000	0,000
	0,399	5,032	0,399	0,000	0,000
	0,598	4,969	0,598	0,000	0,000
	0,797	4,905	0,797	0,000	0,000
	0,997	4,841	0,997	0,000	0,000
	1,196	4,777	1,196	0,000	0,000
	1,395	4,713	1,395	0,000	0,000
	1,594	4,650	1,594	0,000	0,000
	1,794	4,586	1,794	0,000	0,000
	1,993	4,522	1,993	0,000	0,000
	2,192	4,458	2,192	0,000	0,000
	2,392	4,394	2,392	0,000	0,000
	2,591	4,331	2,591	0,000	0,000
	2,790	4,267	2,790	0,000	0,000
	2,990	4,203	2,990	0,000	0,000
	3,189	4,139	3,189	0,000	0,000
	3,388	4,076	3,388	0,000	0,000
	3,588	4,012	3,588	0,000	0,000
	3,787	3,948	3,787	0,000	0,000
	3,986	3,884	3,986	0,000	0,000
	4,186	3,820	4,186	0,000	0,000
	4,385	3,757	4,385	0,000	0,000
	4,584	3,693	4,584	0,000	0,000
	4,783	3,629	4,783	0,000	0,000
	4,983	3,565	4,983	0,000	0,000
	5,182	3,501	5,182	0,000	0,000
	5,381	3,438	5,381	0,000	0,000
	5,581	3,374	5,581	0,000	0,000
	5,780	3,310	5,780	0,000	0,000
	=====================================
	Overall wing derived data
	Span: 5.779999999999999 m
	Semi-span: 5.779999999999999 m
	Surface of planform: 24.47829999999999 m²
	Surface wetted: 48.95659999999998 m²
	Aspect-ratio: 1.3648170011806378
	Mean aerodynamic chord: 4.3023455276363389 m
	(X,Y,Z)_LE of mean aerodynamic chord: [2.6795907298713209 m, 2.6795907298713226 m, 0.0 m]
	Symmetric Flaps Control surface area: 18.265148999999987 m²
	Slats Control surface area: 0.0 m²
	Asymmetric Flaps Control surface area: 0.0 m²
	Spoilers Control surface area: 0.0 m²
	Total Control surface area: 18.265148999999983 m²
	Transition point upper surface: 0.12
	Transition point lower surface: 0.12
	-------------------------------------
	Lifting surface
	-------------------------------------
	ID: 'IRON Canard'
	Type: CANARD
	-------------------------------------
	No. panels = 1
	Main spar position referred to chord = 0.25
	Secondary spar position referred to chord = 0.55
	Surface roughness = 0.00000405 m
	-------------------------------------
	Lifting surface panel
	-------------------------------------
	ID: 'Canard panel'
	Span = 3.75 m
	Lambda_LE = 10.0 deg
	Lambda_c/4 = 9.999999999999996 deg
	Lambda_c/2 = 9.999999999999994 deg
	Lambda_TE = 9.9999999999999929 deg
	Lambda_TE = 9.9999999999999929 deg
	.....................................
	                           panel root
	c_r = 1.9032499999999999 m
	epsilon_r = 0.0 deg
	-------------------------------------
	Airfoil
	-------------------------------------
	Name: Canard_Airfoil_IRON
	Type: SUPERCRITICAL
	t/c = 0.12
	r_le/c = 0.03
	x coordinates = [1.0, 0.994208, 0.983587, 0.970798, 0.956427, 0.941252, 0.925801, 0.910215, 0.894556, 0.878941, 0.863401, 0.847895, 0.832397, 0.816918, 0.801452, 0.786004, 0.770585, 0.755192, 0.739821, 0.724468, 0.709129, 0.6938, 0.678484, 0.663176, 0.647873, 0.632597, 0.617384, 0.60221, 0.587087, 0.571996, 0.556855, 0.541661, 0.526412, 0.511084, 0.495684, 0.480249, 0.464795, 0.449349, 0.433891, 0.418421, 0.402966, 0.387484, 0.371993, 0.356511, 0.341033, 0.32557, 0.310133, 0.294712, 0.279338, 0.264019, 0.24873, 0.233523, 0.218391, 0.203379, 0.188502, 0.173742, 0.159149, 0.144695, 0.130433, 0.116368, 0.102578, 0.089184, 0.076345, 0.064329, 0.053456, 0.043875, 0.035633, 0.028676, 0.022893, 0.01815, 0.01426, 0.011055, 0.008402, 0.0062, 0.00438, 0.002907, 0.001746, 8.81E-4, 3.03E-4, 2.8E-5, 2.7E-5, 2.83E-4, 8.15E-4, 0.001665, 0.002859, 0.004395, 0.006284, 0.008563, 0.011271, 0.014472, 0.018297, 0.022963, 0.028803, 0.03627, 0.045771, 0.057332, 0.070435, 0.084346, 0.098654, 0.113341, 0.128375, 0.143594, 0.15885, 0.174089, 0.189316, 0.204544, 0.219775, 0.235019, 0.25028, 0.26556, 0.280853, 0.296143, 0.311415, 0.326674, 0.341933, 0.357201, 0.372483, 0.38778, 0.403079, 0.418358, 0.433583, 0.448704, 0.463726, 0.478701, 0.493556, 0.50848, 0.523662, 0.539055, 0.554648, 0.57041, 0.586244, 0.60204, 0.617734, 0.633272, 0.648642, 0.663863, 0.678953, 0.693951, 0.708876, 0.723738, 0.738564, 0.753376, 0.768189, 0.78301, 0.797835, 0.812632, 0.827362, 0.842008, 0.856571, 0.871114, 0.885791, 0.900668, 0.915513, 0.930046, 0.944494, 0.958879, 0.972242, 0.984185, 0.994239, 1.0]
	z coordinates = [-0.002003, -7.64E-4, 0.001585, 0.00449, 0.007778, 0.011251, 0.014783, 0.018313, 0.021838, 0.025327, 0.028755, 0.032114, 0.035408, 0.038631, 0.04178, 0.044851, 0.047834, 0.050723, 0.053511, 0.056194, 0.058768, 0.061229, 0.063572, 0.065794, 0.067894, 0.069866, 0.071695, 0.073371, 0.074887, 0.076226, 0.0774, 0.078418, 0.079284, 0.080009, 0.080607, 0.081083, 0.081439, 0.081675, 0.081785, 0.081777, 0.081646, 0.081393, 0.081026, 0.080543, 0.079943, 0.079228, 0.078394, 0.077439, 0.076365, 0.07516, 0.073823, 0.072354, 0.07074, 0.06898, 0.067054, 0.064952, 0.062664, 0.060171, 0.057472, 0.054549, 0.051417, 0.048078, 0.044567, 0.040946, 0.037298, 0.033653, 0.030086, 0.026683, 0.023577, 0.02081, 0.018328, 0.016059, 0.013936, 0.011916, 0.009968, 0.008063, 0.006192, 0.004353, 0.002548, 7.95E-4, -9.18E-4, -0.002657, -0.004416, -0.00615, -0.007813, -0.009377, -0.010811, -0.012083, -0.013212, -0.014273, -0.015321, -0.016413, -0.01762, -0.019061, -0.020829, -0.022873, -0.025043, -0.027155, -0.029083, -0.030824, -0.032426, -0.033913, -0.035275, -0.036493, -0.037561, -0.038476, -0.039239, -0.039848, -0.040307, -0.040618, -0.040783, -0.040805, -0.040679, -0.040403, -0.039974, -0.039395, -0.038667, -0.037796, -0.036786, -0.03564, -0.034359, -0.032935, -0.031349, -0.029591, -0.027656, -0.025495, -0.023131, -0.020618, -0.017992, -0.015294, -0.012569, -0.009861, -0.007204, -0.004633, -0.00218, 1.27E-4, 0.002269, 0.00423, 0.006002, 0.007574, 0.008937, 0.01009, 0.011032, 0.011763, 0.012287, 0.012602, 0.0127, 0.012569, 0.012192, 0.01155, 0.010648, 0.009531, 0.008253, 0.006791, 0.005068, 0.003205, 0.001342, -3.5E-4, -0.001528, -0.002003]
	alpha_0l = -4.6952296658792108 deg
	alpha_star = 7.0 deg
	alpha_stall = 11.0 deg
	Cl_alpha = 0.11791666699999998 1/deg
	Cl0 = 0.553645833
	Cl_star = 1.365416667
	Cl_max = 1.750416667
	Alpha for Cl curve (deg) = [0.0 deg, 1.0 deg, 2.0 deg, 3.0 deg, 4.0 deg, 5.0 deg, 6.0 deg, 7.0 deg, 8.0 deg, 9.0 deg, 10.0 deg, 11.0 deg, 13.0 deg]
	Cl curve (deg) = [0.553645833, 0.670208333, 0.789479167, 0.905520833, 1.021979167, 1.136458333, 1.2515625, 1.365416667, 1.475104167, 1.5809375, 1.6825, 1.750416667, 1.7465625]
	Cd_min = 0.0040625
	Cl @ Cd_min = 0.553645833
	k-factor (drag polar) = 0.0053800142724149186
	Cl for Cd curve (deg) = [0.553645833, 0.670208333, 0.789479167, 0.905520833, 1.021979167, 1.136458333, 1.2515625, 1.365416667, 1.475104167, 1.5809375, 1.6825, 1.750416667]
	Cd curve (deg) = [0.0040625, 0.005, 0.005729167, 0.006770833, 0.007604167, 0.008541667, 0.009375, 0.010104167, 0.011041667, 0.0121875, 0.0134375, 0.015416667]
	Cm_alpha = 684.39824282196196 1/deg
	Cm_ac = -0.138958333
	Cm_ac @ stall = -0.114583333
	Cl for Cm curve (deg) = [0.553645833, 0.670208333, 0.789479167, 0.905520833, 1.021979167, 1.136458333, 1.2515625, 1.365416667, 1.475104167, 1.5809375, 1.6825, 1.750416667]
	Cm curve (deg) = [-0.138958333, -0.1384375, -0.138333333, -0.1375, -0.136770833, -0.135625, -0.134479167, -0.133125, -0.1309375, -0.128229167, -0.110833333, -0.114583333]
	x_ac/c = 0.26
	M_cr = 0.57	Transition point upper side = 0.04
	Transition point lower side = 0.09

	.....................................
	                            panel tip
	c_t = 1.9032499999999999 m
	epsilon_t = 0.0 deg
	-------------------------------------
	Airfoil
	-------------------------------------
	Name: Canard_Airfoil_IRON
	Type: SUPERCRITICAL
	t/c = 0.12
	r_le/c = 0.03
	x coordinates = [1.0, 0.994208, 0.983587, 0.970798, 0.956427, 0.941252, 0.925801, 0.910215, 0.894556, 0.878941, 0.863401, 0.847895, 0.832397, 0.816918, 0.801452, 0.786004, 0.770585, 0.755192, 0.739821, 0.724468, 0.709129, 0.6938, 0.678484, 0.663176, 0.647873, 0.632597, 0.617384, 0.60221, 0.587087, 0.571996, 0.556855, 0.541661, 0.526412, 0.511084, 0.495684, 0.480249, 0.464795, 0.449349, 0.433891, 0.418421, 0.402966, 0.387484, 0.371993, 0.356511, 0.341033, 0.32557, 0.310133, 0.294712, 0.279338, 0.264019, 0.24873, 0.233523, 0.218391, 0.203379, 0.188502, 0.173742, 0.159149, 0.144695, 0.130433, 0.116368, 0.102578, 0.089184, 0.076345, 0.064329, 0.053456, 0.043875, 0.035633, 0.028676, 0.022893, 0.01815, 0.01426, 0.011055, 0.008402, 0.0062, 0.00438, 0.002907, 0.001746, 8.81E-4, 3.03E-4, 2.8E-5, 2.7E-5, 2.83E-4, 8.15E-4, 0.001665, 0.002859, 0.004395, 0.006284, 0.008563, 0.011271, 0.014472, 0.018297, 0.022963, 0.028803, 0.03627, 0.045771, 0.057332, 0.070435, 0.084346, 0.098654, 0.113341, 0.128375, 0.143594, 0.15885, 0.174089, 0.189316, 0.204544, 0.219775, 0.235019, 0.25028, 0.26556, 0.280853, 0.296143, 0.311415, 0.326674, 0.341933, 0.357201, 0.372483, 0.38778, 0.403079, 0.418358, 0.433583, 0.448704, 0.463726, 0.478701, 0.493556, 0.50848, 0.523662, 0.539055, 0.554648, 0.57041, 0.586244, 0.60204, 0.617734, 0.633272, 0.648642, 0.663863, 0.678953, 0.693951, 0.708876, 0.723738, 0.738564, 0.753376, 0.768189, 0.78301, 0.797835, 0.812632, 0.827362, 0.842008, 0.856571, 0.871114, 0.885791, 0.900668, 0.915513, 0.930046, 0.944494, 0.958879, 0.972242, 0.984185, 0.994239, 1.0]
	z coordinates = [-0.002003, -7.64E-4, 0.001585, 0.00449, 0.007778, 0.011251, 0.014783, 0.018313, 0.021838, 0.025327, 0.028755, 0.032114, 0.035408, 0.038631, 0.04178, 0.044851, 0.047834, 0.050723, 0.053511, 0.056194, 0.058768, 0.061229, 0.063572, 0.065794, 0.067894, 0.069866, 0.071695, 0.073371, 0.074887, 0.076226, 0.0774, 0.078418, 0.079284, 0.080009, 0.080607, 0.081083, 0.081439, 0.081675, 0.081785, 0.081777, 0.081646, 0.081393, 0.081026, 0.080543, 0.079943, 0.079228, 0.078394, 0.077439, 0.076365, 0.07516, 0.073823, 0.072354, 0.07074, 0.06898, 0.067054, 0.064952, 0.062664, 0.060171, 0.057472, 0.054549, 0.051417, 0.048078, 0.044567, 0.040946, 0.037298, 0.033653, 0.030086, 0.026683, 0.023577, 0.02081, 0.018328, 0.016059, 0.013936, 0.011916, 0.009968, 0.008063, 0.006192, 0.004353, 0.002548, 7.95E-4, -9.18E-4, -0.002657, -0.004416, -0.00615, -0.007813, -0.009377, -0.010811, -0.012083, -0.013212, -0.014273, -0.015321, -0.016413, -0.01762, -0.019061, -0.020829, -0.022873, -0.025043, -0.027155, -0.029083, -0.030824, -0.032426, -0.033913, -0.035275, -0.036493, -0.037561, -0.038476, -0.039239, -0.039848, -0.040307, -0.040618, -0.040783, -0.040805, -0.040679, -0.040403, -0.039974, -0.039395, -0.038667, -0.037796, -0.036786, -0.03564, -0.034359, -0.032935, -0.031349, -0.029591, -0.027656, -0.025495, -0.023131, -0.020618, -0.017992, -0.015294, -0.012569, -0.009861, -0.007204, -0.004633, -0.00218, 1.27E-4, 0.002269, 0.00423, 0.006002, 0.007574, 0.008937, 0.01009, 0.011032, 0.011763, 0.012287, 0.012602, 0.0127, 0.012569, 0.012192, 0.01155, 0.010648, 0.009531, 0.008253, 0.006791, 0.005068, 0.003205, 0.001342, -3.5E-4, -0.001528, -0.002003]
	alpha_0l = -4.6952296658792108 deg
	alpha_star = 7.0 deg
	alpha_stall = 11.0 deg
	Cl_alpha = 0.11791666699999998 1/deg
	Cl0 = 0.553645833
	Cl_star = 1.365416667
	Cl_max = 1.750416667
	Alpha for Cl curve (deg) = [0.0 deg, 1.0 deg, 2.0 deg, 3.0 deg, 4.0 deg, 5.0 deg, 6.0 deg, 7.0 deg, 8.0 deg, 9.0 deg, 10.0 deg, 11.0 deg, 13.0 deg]
	Cl curve (deg) = [0.553645833, 0.670208333, 0.789479167, 0.905520833, 1.021979167, 1.136458333, 1.2515625, 1.365416667, 1.475104167, 1.5809375, 1.6825, 1.750416667, 1.7465625]
	Cd_min = 0.0040625
	Cl @ Cd_min = 0.553645833
	k-factor (drag polar) = 0.0053800142724149186
	Cl for Cd curve (deg) = [0.553645833, 0.670208333, 0.789479167, 0.905520833, 1.021979167, 1.136458333, 1.2515625, 1.365416667, 1.475104167, 1.5809375, 1.6825, 1.750416667]
	Cd curve (deg) = [0.0040625, 0.005, 0.005729167, 0.006770833, 0.007604167, 0.008541667, 0.009375, 0.010104167, 0.011041667, 0.0121875, 0.0134375, 0.015416667]
	Cm_alpha = 684.39824282196196 1/deg
	Cm_ac = -0.138958333
	Cm_ac @ stall = -0.114583333
	Cl for Cm curve (deg) = [0.553645833, 0.670208333, 0.789479167, 0.905520833, 1.021979167, 1.136458333, 1.2515625, 1.365416667, 1.475104167, 1.5809375, 1.6825, 1.750416667]
	Cm curve (deg) = [-0.138958333, -0.1384375, -0.138333333, -0.1375, -0.136770833, -0.135625, -0.134479167, -0.133125, -0.1309375, -0.128229167, -0.110833333, -0.114583333]
	x_ac/c = 0.26
	M_cr = 0.57	Transition point upper side = 0.04
	Transition point lower side = 0.09

	.....................................
	                   panel derived data
	S = 5.897343749999997 m²
	S_wet = 11.794687499999995 m²
	lambda = 0.9999999999999999
	AR = 2.3845481281297194
	c_MAC = 1.9032499999999994 m
	X_LE_MAC = 0.16530654441418582 m
	Y_LE_MAC = 0.93749999999999978 m
	Z_LE_MAC = 0.0 m
	-------------------------------------
	Symmetric flap
	-------------------------------------
	ID: 'Control Surface'
	Flap type = PLAIN
	Inner station spanwise position = 0.1
	Outer station spanwise position = 1.0
	Inner chord ratio = 0.3
	Outer chord ratio = 0.3
	Mean chord ratio = 0.3
	Minimum deflection = -25.0
	Maximum deflection = 5.0
	.....................................
	=====================================================
	Spanwise discretized CANARD, size 30
	........................................................................................................................
	Y(m),	chord(m),		Xle(m),	Zle(m),	twist(deg)
	........................................................................................................................
	0,000	1,903	0,000	0,000	0,000
	0,129	1,880	0,023	0,000	0,000
	0,259	1,858	0,046	0,000	0,000
	0,388	1,835	0,068	0,000	0,000
	0,517	1,812	0,091	0,000	0,000
	0,647	1,789	0,114	0,000	0,000
	0,776	1,766	0,137	0,000	0,000
	0,905	1,744	0,160	0,000	0,000
	1,034	1,721	0,182	0,000	0,000
	1,164	1,698	0,205	0,000	0,000
	1,293	1,675	0,228	0,000	0,000
	1,422	1,652	0,251	0,000	0,000
	1,552	1,630	0,274	0,000	0,000
	1,681	1,607	0,296	0,000	0,000
	1,810	1,584	0,319	0,000	0,000
	1,940	1,561	0,342	0,000	0,000
	2,069	1,538	0,365	0,000	0,000
	2,198	1,516	0,388	0,000	0,000
	2,328	1,493	0,410	0,000	0,000
	2,457	1,470	0,433	0,000	0,000
	2,586	1,447	0,456	0,000	0,000
	2,716	1,424	0,479	0,000	0,000
	2,845	1,402	0,502	0,000	0,000
	2,974	1,379	0,524	0,000	0,000
	3,103	1,356	0,547	0,000	0,000
	3,233	1,333	0,570	0,000	0,000
	3,362	1,310	0,593	0,000	0,000
	3,491	1,288	0,616	0,000	0,000
	3,621	1,265	0,638	0,000	0,000
	3,750	1,242	0,661	0,000	0,000
	=====================================
	Overall wing derived data
	Span: 7.499999999999999 m
	Semi-span: 3.75 m
	Surface of planform: 11.794687499999995 m²
	Surface wetted: 23.58937499999999 m²
	Aspect-ratio: 4.76909625625944
	Mean aerodynamic chord: 1.5957949401755238 m
	(X,Y,Z)_LE of mean aerodynamic chord: [0.3074439833783946 m, 1.7436014734847398 m, 0.0 m]
	Symmetric Flaps Control surface area: 3.6576899999999997 m²
	Slats Control surface area: 0.0 m²
	Asymmetric Flaps Control surface area: 0.0 m²
	Spoilers Control surface area: 0.0 m²
	Total Control surface area: 3.6576899999999988 m²
	Transition point upper surface: 0.04
	Transition point lower surface: 0.09
	-------------------------------------
	Configuration
	-------------------------------------
	ID: 'IRON Cabin Configuration'
	.....................................
	Actual number of passengers: 130
	Maximum number of passengers: 130
	Flight crew number: 2
	Cabin crew number: 3
	Total crew number: 5
	Classes number: 1
	Classes type: []
	Aisles number: 0
	X coordinates first row: 5.064 m
	Missing seats each row: 

	.....................................
	Number of breaks economy class: 0
	Number of breaks business class: 0
	Number of breaks first class: 0
	Number of rows economy class: 26
	Number of rows business class: 0
	Number of rows first class: 0
	Number of columns economy class: [3, 2]
	Number of columns business class: null
	Number of columns first class: null
	Pitch economy class: 0.8 m
	Pitch business class: 0.0 m
	Pitch first class: 0.0 m
	Width economy class: 0.46999999999999997 m
	Width business class: 0.0 m
	Width first class: 0.0 m
	Distance from wall economy class: 0.1 m
	Distance from wall business class: 0.0 m
	Distance from wall first class: 0.0 m
	.....................................
	-------------------------------------
	Fuel tank
	-------------------------------------
	ID: 'null'
	�������������������������������������
	Main spar position (% local chord): 0.25
	Secondary spar position (% local chord): 0.55
	�������������������������������������
	Airfoils thickness at main spar stations: [0.6602368171874997 m, 0.5141799140624998 m, 0.27447515044518833 m]
	Airfoils thickness at secondary spar stations: [0.57907302014910167 m, 0.4509710879265013 m, 0.24073355224453769 m]
	Spar distance at each spanwise station: [1.2758399999999996 m, 0.9936 m, 0.5881609084593573 m]
	Prismoids length: [5.151175326550149 m, 9.443821432008604 m]
	�������������������������������������
	Prismoids spanwise sections areas: [0.79058053143376417 m², 0.4794870177881356 m², 0.15151280931007804 m²]
	Prismoids volumes: [3.2379544211347095 m³, 2.834825997544458 m³]
	�������������������������������������
	Total tank volume: 12.145560837358332 m³
	Fuel density: 804.0 kg/m³
	Total fuel mass: 9765.030913236096 kg
	Total fuel weight: 95762.24040528675 N
	�������������������������������������
	-------------------------------------
	The Power Plant
	-------------------------------------
	Number of engines: 2
	-------------------------------------
	Engine n� 1
	-------------------------------------
	ID: 'IRON Engine'
	Type: TURBOPROP
	Engine database name: Normalized_TurboProp_100%Cruise_ISA0.h5
	�������������������������������������
	Length: 4.371 m
	Propeller diameter: 3.6499999999999995 m
	Number of blades: 6
	Number of compressor stages: 5
	Number of shafts: 2
	Overall pressure ratio: 15.0
	�������������������������������������
	P0: 7177.0 hp
	T0: 20095.599999999999 lbf
	�������������������������������������
	-------------------------------------
	Engine n� 2
	-------------------------------------
	ID: 'IRON Engine'
	Type: TURBOPROP
	Engine database name: Normalized_TurboProp_100%Cruise_ISA0.h5
	�������������������������������������
	Length: 4.371 m
	Propeller diameter: 3.6499999999999995 m
	Number of blades: 6
	Number of compressor stages: 5
	Number of shafts: 2
	Overall pressure ratio: 15.0
	�������������������������������������
	P0: 7177.0 hp
	T0: 20095.599999999999 lbf
	�������������������������������������
	-------------------------------------
	Nacelles
	-------------------------------------
	Number of nacelles: 2
	-------------------------------------
	Nacelle n� 1
	-------------------------------------
	ID: 'IRON Nacelle'
	�������������������������������������
	Engine ID: 'IRON Engine'
	Engine type: TURBOPROP
	Length: 4.371 m
	Diameter max: 1.3999999999999999 m
	K_inlet: 0.857
	K_outlet: 0.143
	Diameter inlet: 1.1997999999999998 m
	Diameter outlet: 0.20019999999999993 m
	K_length: 0.44
	X position of the max diameter in LRF: 1.9232399999999998 m
	K_diameter_outlet: 1.28
	Z position of the outlet diameter in LRF: 1.7919999999999996 m
	�������������������������������������
	Surface roughness: 0.00000405 m
	Surface wetted: 19.224662084377375 m²
	�������������������������������������
	Discretization
	Outline XY - X (m): [0.0, 0.2300526315789474, 0.4601052631578948, 0.6901578947368421, 0.9202105263157896, 1.150263157894737, 1.3803157894736846, 1.6103684210526321, 1.8404210526315796, 2.070473684210527, 2.300526315789474, 2.530578947368422, 2.760631578947369, 2.990684210526317, 3.2207368421052642, 3.450789473684212, 3.6808421052631592, 3.910894736842107, 4.140947368421054, 4.371]
	Outline XY Left Top View - Y (m): [-0.5998999999999999, -0.626696671924081, -0.6522023227610703, -0.6751259314238756, -0.6941764768254051, -0.7080629378785668, -0.7154942934962687, -0.7151795225914193, -0.7058276040769258, -0.6862482411013682, -0.6565430677628972, -0.6177085310228476, -0.5707590045925057, -0.5167088621831584, -0.45657247750609165, -0.3913642242725923, -0.32209847619394694, -0.24978960698144198, -0.17545199034636416, -0.10009999999999997]
	Outline XY Right Top View - Y (m): [0.5998999999999999, 0.626696671924081, 0.6522023227610703, 0.6751259314238756, 0.6941764768254051, 0.7080629378785668, 0.7154942934962687, 0.7151795225914193, 0.7058276040769258, 0.6862482411013682, 0.6565430677628972, 0.6177085310228476, 0.5707590045925057, 0.5167088621831584, 0.45657247750609165, 0.3913642242725923, 0.32209847619394694, 0.24978960698144198, 0.17545199034636416, 0.10009999999999997]
	Outline XZ Upper Side View - Z (m): [0.5998999999999999, 0.5901741997905869, 0.5823383351668012, 0.5782823417142704, 0.5798961550186217, 0.5890697106654825, 0.6076929442404801, 0.6376557913292422, 0.6808481875173957, 0.7390126174161165, 0.812000298096349, 0.8983525232749465, 0.996584343563202, 1.1052108095724078, 1.2227469719138573, 1.3477078811988425, 1.4786085880386568, 1.6139641430445928, 1.7522895968279428, 1.8920999999999997]
	Outline XZ Lower Side View - Z (m): [-0.5998999999999999, -0.6632191440575752, -0.7220663103553391, -0.7719695211334807, -0.8084567986321884, -0.827056165091651, -0.8232956427520572, -0.7927032538535961, -0.7308070206364559, -0.6334838647866197, -0.5010858374294453, -0.3370645387707487, -0.14493366562180976, 0.07179308520609118, 0.3096020169016739, 0.5649794326536577, 0.8344116356507627, 1.1143849290817087, 1.4013856161352147, 1.6918999999999995]
	�������������������������������������
	-------------------------------------
	Nacelle n� 2
	-------------------------------------
	ID: 'IRON Nacelle'
	�������������������������������������
	Engine ID: 'IRON Engine'
	Engine type: TURBOPROP
	Length: 4.371 m
	Diameter max: 1.3999999999999999 m
	K_inlet: 0.857
	K_outlet: 0.143
	Diameter inlet: 1.1997999999999998 m
	Diameter outlet: 0.20019999999999993 m
	K_length: 0.44
	X position of the max diameter in LRF: 1.9232399999999998 m
	K_diameter_outlet: 1.28
	Z position of the outlet diameter in LRF: 1.7919999999999996 m
	�������������������������������������
	Surface roughness: 0.00000405 m
	Surface wetted: 19.224662084377375 m²
	�������������������������������������
	Discretization
	Outline XY - X (m): [0.0, 0.2300526315789474, 0.4601052631578948, 0.6901578947368421, 0.9202105263157896, 1.150263157894737, 1.3803157894736846, 1.6103684210526321, 1.8404210526315796, 2.070473684210527, 2.300526315789474, 2.530578947368422, 2.760631578947369, 2.990684210526317, 3.2207368421052642, 3.450789473684212, 3.6808421052631592, 3.910894736842107, 4.140947368421054, 4.371]
	Outline XY Left Top View - Y (m): [-0.5998999999999999, -0.626696671924081, -0.6522023227610703, -0.6751259314238756, -0.6941764768254051, -0.7080629378785668, -0.7154942934962687, -0.7151795225914193, -0.7058276040769258, -0.6862482411013682, -0.6565430677628972, -0.6177085310228476, -0.5707590045925057, -0.5167088621831584, -0.45657247750609165, -0.3913642242725923, -0.32209847619394694, -0.24978960698144198, -0.17545199034636416, -0.10009999999999997]
	Outline XY Right Top View - Y (m): [0.5998999999999999, 0.626696671924081, 0.6522023227610703, 0.6751259314238756, 0.6941764768254051, 0.7080629378785668, 0.7154942934962687, 0.7151795225914193, 0.7058276040769258, 0.6862482411013682, 0.6565430677628972, 0.6177085310228476, 0.5707590045925057, 0.5167088621831584, 0.45657247750609165, 0.3913642242725923, 0.32209847619394694, 0.24978960698144198, 0.17545199034636416, 0.10009999999999997]
	Outline XZ Upper Side View - Z (m): [0.5998999999999999, 0.5901741997905869, 0.5823383351668012, 0.5782823417142704, 0.5798961550186217, 0.5890697106654825, 0.6076929442404801, 0.6376557913292422, 0.6808481875173957, 0.7390126174161165, 0.812000298096349, 0.8983525232749465, 0.996584343563202, 1.1052108095724078, 1.2227469719138573, 1.3477078811988425, 1.4786085880386568, 1.6139641430445928, 1.7522895968279428, 1.8920999999999997]
	Outline XZ Lower Side View - Z (m): [-0.5998999999999999, -0.6632191440575752, -0.7220663103553391, -0.7719695211334807, -0.8084567986321884, -0.827056165091651, -0.8232956427520572, -0.7927032538535961, -0.7308070206364559, -0.6334838647866197, -0.5010858374294453, -0.3370645387707487, -0.14493366562180976, 0.07179308520609118, 0.3096020169016739, 0.5649794326536577, 0.8344116356507627, 1.1143849290817087, 1.4013856161352147, 1.6918999999999995]
	�������������������������������������
	-------------------------------------
	Landing gears
	-------------------------------------
	ID: 'IRON Landing Gears'
	�������������������������������������
	Main gear legs length: 1.6 m
	Distance between wheels: 5.0 m
	Number of frontal wheels: 2
	Number of rear wheels: 4
	�������������������������������������
	Frontal wheels height: 0.96999999999999997 m
	Frontal wheels width: 0.34999999999999998 m
	�������������������������������������
	Rear wheels height: 0.96999999999999997 m
	Rear wheels width: 0.34999999999999998 m
	�������������������������������������

Out[6]:
null

Have a look at the output of the above cell! Such a huge amount of data represents the geometry and the basic aerodynamic characteristics of the chosen aircraft design.