Open jayeye2011 opened 1 year ago
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
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