Airfoil Data
MH126
MH 126 25.0%
Wing Geometry Simulator
The MH 126 25.0% is a thick 20.1% chord-thickness airfoil with a maximum camber of 10.1% at 41% chord, suited to high-lift UAV wings, RC sailplanes, and low-Reynolds-number slow-flyers. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -10.1°.
Thin airfoil theory predicts a stall angle near 8.8° and a peak lift-to-drag ratio around 79 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 20% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the MH126 typically compare it against profiles of similar thickness: EPPLER 864 STRUT AIRFOIL, GOE 531 AIRFOIL, KENNEDY AND MARSDEN AIRFOIL, S9104, S9104BTE. The EPPLER 546 AIRFOIL is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the MH126 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (20.1%) and max camber (10.1%).
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