Airfoil Data
NACA651212A06
NACA 65(1)-212 a=0.6
Wing Geometry Simulator
The NACA 65(1)-212 a=0.6 is a thin 7.4% chord-thickness airfoil with a maximum camber of 3.7% 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 -3.7°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 56 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 NACA651212A06 typically compare it against profiles of similar thickness: MH 117 9.8%, LOCKHEED C-141 BL0 AIRFOIL, MA409 (original), GOE 766 AIRFOIL, EH 2.5/10. The NACA 11-H-09 AIRFOIL is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the NACA651212A06 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (7.4%) and max camber (3.7%).
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