Airfoil Data
MH61

The MH 61 10.26% is a thin 6.6% chord-thickness airfoil with a maximum camber of 3.3% at 32% chord, suited to high-speed UAVs, sailplane tip sections, and propeller blade design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -3.3°.

Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 54 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 MH61 typically compare it against profiles of similar thickness: LOCKHEED C-5A BL0 AIRFOIL, BOEING 707 .40 SPAN AIRFOIL, GOE 411 AIRFOIL, S8065 (11% version of S8064), MH 45 9.85%. The GOE 227 (MVA H.37) AIRFOIL is another reference profile frequently considered alongside it.