![]() % c = 1 to simplifiy the equation the chord is set to 1 So I sat down, found the equation for NACA. A fellow modeller produced some airfoils in profili for me, but simply none was properly fitting. I was stuck with a Katana plan with the ribs but not the cuts of the whole wing that would help me to produce templates for sanding the leading edge. ![]() The implementation in MATLAB looks like this:ī = 1.0 % caution for NON-unity entries change the equation for h Symmetrical 4-digit NACA airfoil generator in Matlab. However, I am struggling to plot the profile based on the equations given here and here. With the help of Aviation.stackexchange I learned that the A-Version of the profile was created to ease manufacturing by thickening the trailing edge-section (by a straight contour from 80% chord backwards). I would like to calculate the profile NACA 64-2A015. Especially since there were really good answers on the NACA 5-digit-Series airfoil generation. I asked this question over at Aviation.stackexchange but after that I figured it might be better to place it here.
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