Airfoil Data
GOE432
GOE 432 AIRFOIL
Wing Geometry Simulator
The GOE 432 AIRFOIL is a 8.0% chord-thickness airfoil with a maximum camber of 4.0% 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 -4.0°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 58 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 GOE432 typically compare it against profiles of similar thickness: GOE 396 AIRFOIL, GOE 408 AIRFOIL, I.S.A. 571, GOE 442 AIRFOIL, CAL1215j. The RG 14 10% AIRFOIL is another reference profile frequently considered alongside it.
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Engineers evaluating the GOE432 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.0%) and max camber (4.0%).
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