Airfoil Data
FALCON
Falcon
Wing Geometry Simulator
The Falcon is a 8.3% chord-thickness airfoil with a maximum camber of 4.2% at 31% 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 -4.2°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 59 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 FALCON typically compare it against profiles of similar thickness: RAF 34 AIRFOIL, GOE 362 AIRFOIL, GOE 602 AIRFOIL, GOE 602 MOD. AIRFOIL, CAP 21 (TraCFoil). The J5012 12% is another reference profile frequently considered alongside it.
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Engineers evaluating the FALCON frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.3%) and max camber (4.2%).
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