Airfoil Data
GOE425
GOE 425 AIRFOIL
Wing Geometry Simulator
The GOE 425 AIRFOIL is a 12.4% chord-thickness airfoil with a maximum camber of 6.2% at 29% chord, suited to high-lift UAV wings, RC sailplanes, and low-Reynolds-number slow-flyers. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -6.2°.
Thin airfoil theory predicts a stall angle near 11.5° and a peak lift-to-drag ratio around 69 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 12% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the GOE425 typically compare it against profiles of similar thickness: RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL, NACA 2421, GOE 413 AIRFOIL, CLARK YM-18 AIRFOIL, GOE 654 AIRFOIL. The AH 82-150 F is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the GOE425 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (12.4%) and max camber (6.2%).
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