Airfoil Data
SC20403

The NASA SC(2)-0403 AIRFOIL is a thin 1.5% chord-thickness airfoil with a maximum camber of 0.8% at 43% 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 -0.8°.

Thin airfoil theory predicts a stall angle near 12.1° and a peak lift-to-drag ratio around 40 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 SC20403 typically compare it against profiles of similar thickness: NASA SC(2)-0503 AIRFOIL, NASA SC(2)-0402 AIRFOIL, NASA SC(2)-0404 AIRFOIL, GOE 9K AIRFOIL, HT05. The MH 32 8.7% is another reference profile frequently considered alongside it.