Airfoil Data
CLARKW
CLARK W AIRFOIL
Wing Geometry Simulator
The CLARK W AIRFOIL is a 9.1% chord-thickness airfoil with a maximum camber of 4.5% at 40% chord, suited to general-aviation and UAV wing design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -4.5°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 61 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 CLARKW typically compare it against profiles of similar thickness: S4158, GOE 389 AIRFOIL, BOEING 737 ROOT AIRFOIL, MH 201 13.08%, EPPLER 636 AIRFOIL. The NASA NLF(1)-0115 is another reference profile frequently considered alongside it.
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Engineers evaluating the CLARKW frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (9.1%) and max camber (4.5%).
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