Airfoil Data
GOE518
GOE 518 AIRFOIL
Wing Geometry Simulator
The GOE 518 AIRFOIL is a thick 16.3% chord-thickness airfoil with a maximum camber of 8.1% at 30% 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 -8.1°.
Thin airfoil theory predicts a stall angle near 10.1° and a peak lift-to-drag ratio around 74 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 16% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the GOE518 typically compare it against profiles of similar thickness: CH10 (smoothed), GOE 511 AIRFOIL, USA 34 AIRFOIL, IST-MT1-18, Rhode St. Genese 36. The AH 63-K-127/24 is another reference profile frequently considered alongside it.
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Engineers evaluating the GOE518 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (16.3%) and max camber (8.1%).
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