Airfoil Data
GOE310
GOE 310 (MVA H.42) AIRFOIL
Wing Geometry Simulator
The GOE 310 (MVA H.42) AIRFOIL is a 8.7% chord-thickness airfoil with a maximum camber of 4.3% at 40% 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 -4.3°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 60 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 GOE310 typically compare it against profiles of similar thickness: K3311 (smoothed), GOE 177 AIRFOIL, SIKORSKY SC1012R8 AIRFOIL, GOE 178 AIRFOIL, SG6042. The SELIG 3002-099-83 is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the GOE310 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.7%) and max camber (4.3%).
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