Airfoil Data
NACA652415A05
NACA 65(2)-415 a=0.5
Wing Geometry Simulator
The NACA 65(2)-415 a=0.5 is a 10.5% chord-thickness airfoil with a maximum camber of 5.2% 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 -5.2°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 65 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 10% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the NACA652415A05 typically compare it against profiles of similar thickness: S1221 w/o flap, S1221 w/ 4 deg flap, 20-32C AIRFOIL, NACA M23 AIRFOIL, AH 80-129. The NACA M18 AIRFOIL is another reference profile frequently considered alongside it.
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Engineers evaluating the NACA652415A05 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.5%) and max camber (5.2%).
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