Airfoil Data
GOE633
GOE 633 AIRFOIL
Wing Geometry Simulator
The GOE 633 AIRFOIL is a 10.7% chord-thickness airfoil with a maximum camber of 5.4% 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 -5.4°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 65 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the GOE633 typically compare it against profiles of similar thickness: GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL, FX 60-160 AIRFOIL, USA 40 AIRFOIL, FX 61-163 AIRFOIL, MRC-20. The MH 45 9.85% is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the GOE633 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.7%) and max camber (5.4%).
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