Airfoil Data
GOE703
GOE 703 AIRFOIL
Wing Geometry Simulator
The GOE 703 AIRFOIL is a 12.0% chord-thickness airfoil with a maximum camber of 6.0% 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 -6.0°.
Thin airfoil theory predicts a stall angle near 11.6° 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 GOE703 typically compare it against profiles of similar thickness: Bambino 6, RAF 6 AIRFOIL, 12%, LE rad. 0.012, TE rad. 0.0092, NACA TR259 smoothed, NACA 0024, DAE-31 AIRFOIL, EPPLER 1214 AIRFOIL. The NACA 23015 is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the GOE703 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (12.0%) and max camber (6.0%).
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