Airfoil Data
WHITCOMB
WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL
Wing Geometry Simulator
The WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL is a thin 5.5% chord-thickness airfoil with a maximum camber of 2.8% 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 -2.8°.
Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 51 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 WHITCOMB typically compare it against profiles of similar thickness: NASA/LANGLEY RC-SC2 AIRFOIL, W1011, NASA/LANGLEY RC-08(N)1 AIRFOIL, GIII BL126 AIRFOIL, NLR-7223-62 AIRFOIL. The SG6050 is another reference profile frequently considered alongside it.
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Engineers evaluating the WHITCOMB frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (5.5%) and max camber (2.8%).
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