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1. #NACA AIRFOIL GENERATOR 6 HOW TO#
2. #NACA AIRFOIL GENERATOR 6 CODE#
3. #NACA AIRFOIL GENERATOR 6 SERIES#
4. #NACA AIRFOIL GENERATOR 6 DOWNLOAD#

This option allows you to specify whether the trailing edge of the airfoil is closed or open. I would always recommend using the non-uniform grid type. This is particularly useful in the vortex panel method, where the pressure coefficient is highly dependent on accuracy at the LE and TE. This allows you to resolve the LE and TE better for the same amount of data points. The non-uniform grid type clusters more points at the leading edge (LE) and trailing edge (TE) of the airfoil. The uniform grid type splits the X values of the airfoil evenly from 0 to 1. You can specify either a uniform or non-uniform grid type. Needless to say, you should use larger values of grid points if you want to be able to resolve the shape accurately. With three points, the airfoil will actually be a diamond shape with a little thickness. If you were to use two, the resulting airfoil would be a line. The minimum number of grid points you can use is three. That is, if you specify 10 grid points, there will be 10 points for the upper surface and 10 points for the lower surface, not 10 points total. This value specifies the number of grid points to use for the upper surface and lower surface. This way, you can use the same airfoil coordinate file for any AoA.

#NACA AIRFOIL GENERATOR 6 CODE#

If you are using the coordinate files in a panel code, then you do not want the AoA in the coordinate file it should be set in the panel code itself. The coordinate files are not affected by the AoA. The angle of attack (AoA) setting is there solely for visualization purposes. For the two most well-known airfoils, try 0012 (symmetric) and 2412 (cambered). Any more or less and the program will give you an error. This is a 4-digit airfoil program, and as such, you will need to specify only 4 digits.

#NACA AIRFOIL GENERATOR 6 SERIES#

You can go to the next video in the series after the first one ends, or by going to my channel page. It's nothing major, and you will still be able to follow along.

#NACA AIRFOIL GENERATOR 6 DOWNLOAD#

Note that the code you can download here is slightly different than that in the videos because I have made some updates.

#NACA AIRFOIL GENERATOR 6 HOW TO#

I have made some YouTube videos regarding the math behind the airfoil, as well as how to code it in MATLAB as both a simple script, and in a GUI.įor a video on the math behind the airfoils, click here.įor a video on coding a simple script, click here.įor a 10-video series on creating this GUI, click here for video 1. This is also a useful way to save coordinate files, as you can multiply both the X and Y values by the chord length you desire, while still having only a single coordinate file for each airfoil. The X and Y values are normalized by the chord length. Again, without changing any values, you should be able to press Save Data, and the coordinate file will be saved as NACA.txt to the directory that the code is located in.įor in-depth descriptions of the different aspects of the GUI, see the sections below. With the default values given in the GUI upon startup, you should be able to simply press Plot Airfoil, and the NACA 0012 will appear. If you want to run the code, you will need to download both GUI_NACA_4_Digit_Airfoil.m and GUI_NACA_4_Digit_Airfoil.fig, and place them in the same directory/folder. As this is coded as a GUI, it contains both the. This repository contains the code used to generate NACA 4-digit airfoil coordinate files.