Airfoil Data
ISA962
I.S.A. 962
Wing Geometry Simulator
The I.S.A. 962 is a 10.6% chord-thickness airfoil with a maximum camber of 5.3% at 30% 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 -5.3°.
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 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the ISA962 typically compare it against profiles of similar thickness: NACA 63(2)-615, EPPLER 1213 AIRFOIL, EPPLER EC 86(-3)-914 AIRFOIL, GOE 329 (PFALZ 58) AIRFOIL, GOE 493 AIRFOIL. The NACA 64-108 AIRFOIL is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the ISA962 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.6%) and max camber (5.3%).
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