Airfoil Data
RC10B3

The NASA/LANGLEY RC-10(B)3 AIRFOIL is a thin 6.7% chord-thickness airfoil with a maximum camber of 3.3% 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 -3.3°.

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 RC10B3 typically compare it against profiles of similar thickness: SIKORSKY SC2110 AIRFOIL, HQ 2.1/9.5 AIRFOIL, GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL, MH 32 8.7%, BELL/WORTMANN FX 69-H-098 AIRFOIL. The NACA 64A-010 10.0% is another reference profile frequently considered alongside it.