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NACA 4412 TMD:Airfoil Probably Has Incorrect Parameters #16

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jayeye2011 opened this issue Jan 19, 2023 · 1 comment

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jayeye2011 commented Jan 19, 2023 •

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When I updated the Wilga.tmd.airfoil parameters for the main wings (root and tip) I did not change the pre-existing ClAlpha, CdAlpha, CmAlpha, AttachedCenter, AttachedRange, and StallRange values since I did not understand how these were supposed to be determined. As such, the pre-existing values were retained but are very likely to be incorrect. However these can and should be calculated using the AirfoilTools.com NACA 4412-il polar plots for Reynolds # 1M Ncrit 9
http://airfoiltools.com/polar/details?polar=xf-naca4412-il-1000000
using the instructions provided by Jet-Pack in
https://www.aerofly.com/community/forum/index.php?thread/7264-how-to-create-an-airfoil-mh-30/&postID=33570#post33570

krzysk1 self-assigned this

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krzysk1 commented Dec 2, 2024

Wilga - NACA2415

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