Airfoil Data
GOE460
GOE 460 AIRFOIL
Wing Geometry Simulator
The GOE 460 AIRFOIL is a 10.3% chord-thickness airfoil with a maximum camber of 5.1% 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 -5.1°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 64 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 GOE460 typically compare it against profiles of similar thickness: GOE 601 AIRFOIL, EPPLER 329 AIRFOIL, GOE 575 AIRFOIL, EPPLER 542 AIRFOIL, SG6043. The MH 78 14.47% is another reference profile frequently considered alongside it.
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Engineers evaluating the GOE460 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.3%) and max camber (5.1%).
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