Airfoil Data
MI-VAWT1
MI-VAWT1
Wing Geometry Simulator
The MI-VAWT1 is a 10.9% chord-thickness airfoil with a maximum camber of 5.4% at 31% chord, suited to general-aviation and UAV wing design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -5.4°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 66 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the MI-VAWT1 typically compare it against profiles of similar thickness: GOE 632 AIRFOIL, GOE 319 (HANSA-BRANDENBURG II) AIRFOIL, GOE 701 AIRFOIL, NACA 2418, GOE 497 AIRFOIL. The S1014 is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the MI-VAWT1 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.9%) and max camber (5.4%).
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