Airfoil Data
RC0864C

The NASA/LANGLEY RC08-64C AIRFOIL is a thin 5.0% chord-thickness airfoil with a maximum camber of 2.5% 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 -2.5°.

Thin airfoil theory predicts a stall angle near 12.0° and a peak lift-to-drag ratio around 49 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 RC0864C typically compare it against profiles of similar thickness: JX-GS-06, AG17, NACA 64A-010 10.0%, NACA 63A010 AIRFOIL, LWK 79-100. The EPPLER 472 AIRFOIL is another reference profile frequently considered alongside it.