Airfoil Data
GOE765
Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300
Wing Geometry Simulator
The Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 is a 9.1% chord-thickness airfoil with a maximum camber of 4.5% at 28% 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 -4.5°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 61 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 GOE765 typically compare it against profiles of similar thickness: NACA 23015, GOE 402 AIRFOIL, GOE 385 AIRFOIL, NACA 66,2-(1.8)15.5 A=.6 P-51 ROOT AIRFOIL, GOE 308 (MVA H.40) AIRFOIL. The GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the GOE765 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (9.1%) and max camber (4.5%).
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