Airfoil Data
MH201

The MH 201 13.08% is a 9.1% chord-thickness airfoil with a maximum camber of 4.5% at 36% 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 11.7° 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 MH201 typically compare it against profiles of similar thickness: BOEING 737 ROOT AIRFOIL, EPPLER 636 AIRFOIL, NACA 66,2-(1.8)15.5 A=.6 P-51 ROOT AIRFOIL, GOE 389 AIRFOIL, NACA 23015. The MB253515 15.0% smoothed is another reference profile frequently considered alongside it.