Airfoil Data
GOE567

The GOE 567 AIRFOIL is a 12.0% chord-thickness airfoil with a maximum camber of 6.0% at 39% 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 -6.0°.

Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 69 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 12% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the GOE567 typically compare it against profiles of similar thickness: USA 33 AIRFOIL, FX 61-184 AIRFOIL, EPPLER 398 AIRFOIL, GOE 627 AIRFOIL, NASA NLF(1)-1015. The GOE 503 AIRFOIL is another reference profile frequently considered alongside it.