Airfoil Data
SC20714

The NASA SC(2)-0714 AIRFOIL is a thin 7.0% chord-thickness airfoil with a maximum camber of 3.5% at 40% 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 -3.5°.

Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 55 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 SC20714 typically compare it against profiles of similar thickness: SG6041, M6 (85%), NASA/LANGLEY RC12-64C AIRFOIL, S1048 14% (Danny Howell), Coanda 1. The USA 31 AIRFOIL is another reference profile frequently considered alongside it.