Airfoil Data
NASASC2-0714
SC(2)-0714 | Supercritical airfoil (coordinates from Raymer w/ one correction). These coordinates are actual model coordinates, not coordinates as designed. Ref: NASA TP-2890
Wing Geometry Simulator
The SC(2)-0714 | Supercritical airfoil (coordinates from Raymer w/ one correction). These coordinates are actual model coordinates, not coordinates as designed. Ref: NASA TP-2890 is a thin 7.0% chord-thickness airfoil with a maximum camber of 3.5% at 38% 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 NASASC2-0714 typically compare it against profiles of similar thickness: S1048 14% (Danny Howell), NASA/LANGLEY RC12-64C AIRFOIL, M6 (85%), NASA SC(2)-0714 AIRFOIL, SD7080 (9.2%). The GW 27 is another reference profile frequently considered alongside it.
Design wings in your spreadsheet
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Related Airfoils
Engineers evaluating the NASASC2-0714 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (7.0%) and max camber (3.5%).
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