Airfoil Data
SA7035
SA7035
Wing Geometry Simulator
The SA7035 is a thin 7.1% chord-thickness airfoil with a maximum camber of 3.5% at 31% 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 -3.5°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 55 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 SA7035 typically compare it against profiles of similar thickness: NASA RC(4)-10 AIRFOIL, SD7084 (9.6%), NACA 65(1)-212, GOE 147 (MVA H.6) AIRFOIL, E178 (8.69%). The NACA M3 is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the SA7035 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (7.1%) and max camber (3.5%).
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