Making airfoil generator code series#
If NACA is True, airfoil is the naca series of the airfoil (i.e.: naca2244). If you want to plot an airfoil, then just head over to NACA. 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. I would like to calculate the profile NACA 64-2A015. You can mess around with the values and see how they change the geometry, keeping everything else the same. Parameters: airfoil if NACA is false, airfoil is the name of the plain filewhere the airfoil geometry is stored (variable airfoil). First, you need an Excel file in which you have all the coordinates of the curve or an airfoil. Especially since there were really good answers on the NACA 5-digit-Series airfoil generation. From the quoted selection, it seems like these coefficients were chosen to closely match the thickness distributions from other airfoils that were known to work well. 6.2 on page 113, which includes these seemingly arbitrary coefficients that you’re asking about. The thickness distribution for the NACA four-digit sections was selected to correspond closely to that for these wing sections and is given by the following equation” The equation stated is Eq. In the section about the NACA 4-digit airfoils (section 6.4, page 113) they state the following: “When the NACA four-digit wing sections were derived, it was found that the thickness distributions of efficient wing sections such as the Gottingen 398 and the Clark Y were nearly the same when their camber was removed (mean line straightened) and they were reduced to the same maximum thickness. “So first of all, if you don’t already have it, I recommend getting the book Theory of Wing Sections by Abbott and Von Doenhoff if you’re interested in wings/airfoils etc. Here’s a response I wrote to someone who had the same question as you.
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