Airfoil Data
RC1064C

The NASA/LANGLEY RC10-64C AIRFOIL is a thin 6.0% chord-thickness airfoil with a maximum camber of 3.0% 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 -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 RC1064C typically compare it against profiles of similar thickness: GIII BL45 AIRFOIL, MH 43 8.5%, NASA/LANGLEY 64-012 AIRFOIL, EPPLER 428 AIRFOIL, WORTMANN FX 71-120 AIRFOIL. The LWK 80-150/K25 is another reference profile frequently considered alongside it.