This report describes a computer program that combines the capabilities of the previously published versions.
Since the publication of these programs, the use of personal computers and individual workstations has proliferated. For the 6-series and all but the leading edge of the 6A-series airfoils, agreement between the ordinates obtained from the program and previously published ordinates is generally within 5 x 10(exp -5) chord. For analytic airfoils, the ordinates are exact. * (a-x).^2) - x.*log(x) + g - h.Computer Program to Obtain Ordinates for NACA Airfoils Computer programs to produce the ordinates for airfoils of any thickness, thickness distribution, or camber in the NACA airfoil series were developed in the early 1970's and are published as NASA TM X-3069 and TM X-3284. % c = 1 to simplifiy the equation the chord is set to 1 The implementation in MATLAB looks like this:ī = 1.0 % caution for NON-unity entries change the equation for h 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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