Airfoil Data
GOE225
GOE 225 (MVA H.35) AIRFOIL
Wing Geometry Simulator
The GOE 225 (MVA H.35) AIRFOIL is a 13.1% chord-thickness airfoil with a maximum camber of 6.5% at 40% chord, suited to high-lift UAV wings, RC sailplanes, and low-Reynolds-number slow-flyers. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -6.5°.
Thin airfoil theory predicts a stall angle near 11.2° and a peak lift-to-drag ratio around 70 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 13% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the GOE225 typically compare it against profiles of similar thickness: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA), GOE 692 AIRFOIL, EPPLER 856 AIRFOIL, GOE 646 AIRFOIL, GOE 675 AIRFOIL. The NACA 66,2-(1.8)15.5 A=.6 P-51 ROOT AIRFOIL is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the GOE225 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (13.1%) and max camber (6.5%).
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