Airfoil Data
JX-GS-06
JX-GS-06
Wing Geometry Simulator
The JX-GS-06 is a thin 5.0% chord-thickness airfoil with a maximum camber of 2.5% at 27% 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 -2.5°.
Thin airfoil theory predicts a stall angle near 12.0° and a peak lift-to-drag ratio around 49 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 JX-GS-06 typically compare it against profiles of similar thickness: NASA/LANGLEY RC08-64C AIRFOIL, AG17, NACA 64A-010 10.0%, NACA 63A010 AIRFOIL, LWK 79-100. The GOE 458 AIRFOIL is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the JX-GS-06 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (5.0%) and max camber (2.5%).
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