Macro AeroFoil

Description
'AeroFoil' is a user-created macro to be used within the FreeCAD application. AeroFoil creates airfoil curves and faces using pre-defined models, algebraic functions, as well as imported DAT or CSV files.

This is the AeroFoil Macro icon.

The AeroFoil Macro project can be found in this GitHub Repository.

Key Features

 * Airfoil points refinement
 * Multiple airfoil copy generation
 * 2D curves and planar face output
 * DWire/PolyLine and BSpline output
 * Sketch workbench and Draft workbench output
 * Ready-made NACA 4-digit and 5-digit solvers
 * Symmetric and asymmetric curve functions parser
 * DAT text file and CSV spreadsheet data parser
 * Chord length input in mm, cm, m, in., ft, and yards

Additional Features
AeroFoil object properties (read-only) :





Linux
AeroFoil can be installed manually, similar to Windows installation, or by using the command terminal and its relevant commands as mentioned in the INSTALL file.

By default, the Linux command terminal can be launched by pressing the following keyboard keys simultaneously :

Windows
AeroFoil can be installed with the help of the following two steps :-


 * 1) Download the AeroFoil.zip file.
 * 2) Extract the ZIP file's contents into the FreeCAD User Macro directory location.

By default, the FreeCAD User Macro directory should be located at :

Usage
AeroFoil can be loaded by performing the following steps :-


 * 1) Launch the FreeCAD application.
 * 2) Go to.
 * 3) Click on the User macros tab in the pop-up dialog box.
 * 4) Select.
 * 5) Click on.

Once the AeroFoil macro has been loaded, follow the instructions in the respective dialog boxes, fill in the relevant inputs, and navigate accordingly. In case of error or warning, you will automatically be notified of the same. In case you are notified to report an unexpected error, communicate the error by mentioning the FreeCAD version, tracing the steps taken, and mentioning whether (and how much) or not any ouput was generated.

Hints to keep in mind during usage :

 * 1) For the NACA airfoils, the last two digits (combined) cannot have a value of zero; thickness cannot be a zero value.
 * 2) The NACA 5-digit airfoils are limited to the following models ('XX' denotes the last two digits, thickness, of the airfoil) :
 * 3) * 210XX
 * 4) * 220XX
 * 5) * 221XX
 * 6) * 230XX
 * 7) * 231XX
 * 8) * 240XX
 * 9) * 241XX
 * 10) * 250XX
 * 11) * 251XX
 * 12) For curve functions, only use the preset characters and functions.
 * 13) For curve functions, $$2 * x$$ is correct, whereas $$2x$$ is incorrect.
 * 14) For curve functions, $$y = f(x)$$ ranges from 0 to 1, both inclusive.
 * 15) For curve functions, the trigonometric theta is in degrees (&theta; &deg;)
 * 16) For curve functions, the trigonometric theta ranges from 0&deg; to 360&deg;, subject to computational limits.
 * 17) Curves or points that are intersecting between 0 and 1, both exclusive, will return an error.
 * 18) Curves or points that contain the bottom airfoil data cannot be mirrored
 * 19) For file imports, it is suggested to leave the line, row, and column numbers to their default values, unless you are well-informed.
 * 20) Increasing the refine and quantity parameters increases the computation time and resources.
 * 21) Absolute chord length, in millimetres, cannot be less than 1mm.