Airfoil Data
SC20412
NASA SC(2)-0412 AIRFOIL
Wing Geometry Simulator
The NASA SC(2)-0412 AIRFOIL is a thin 6.0% chord-thickness airfoil with a maximum camber of 3.0% at 42% 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 -3.0°.
Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 52 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 SC20412 typically compare it against profiles of similar thickness: NASA SC(2)-0712 AIRFOIL, S1012, RG-12, AS6091 | Ananda-Selig | AIAA Paper 2018-0310, E226 (10.19%). The HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the SC20412 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (6.0%) and max camber (3.0%).
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