Airfoil Data
CAL2263M
CAL2263m
Wing Geometry Simulator
The CAL2263m is a 9.3% chord-thickness airfoil with a maximum camber of 4.6% at 35% 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 -4.6°.
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 CAL2263M typically compare it against profiles of similar thickness: NASA NLF(1)-0115, US1000ROOT, GOE 287 AIRFOIL, BOEING VERTOL V43012-1.58 AIRFOIL, EPPLER 502 AIRFOIL. The NASA SC(2)-0714 AIRFOIL is another reference profile frequently considered alongside it.
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Engineers evaluating the CAL2263M frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (9.3%) and max camber (4.6%).
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