Airfoil Data
MH91

The MH 91 14.98% is a 9.0% chord-thickness airfoil with a maximum camber of 4.5% at 26% 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 -4.5°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 61 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The slim profile minimises pressure drag at higher speeds but leaves limited spar depth for structural integration.

Designers evaluating the MH91 typically compare it against profiles of similar thickness: NACA 66-018, NACA 16-018, GOE 559 AIRFOIL, USA-35B AIRFOIL, Dormoy. The NACA 63(4)-421 is another reference profile frequently considered alongside it.