Airfoil Data
GOE592

The GOE 592 AIRFOIL is a 14.5% chord-thickness airfoil with a maximum camber of 7.3% 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 -7.3°.

Thin airfoil theory predicts a stall angle near 10.7° and a peak lift-to-drag ratio around 72 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 15% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the GOE592 typically compare it against profiles of similar thickness: GW 19, GOE 770 AIRFOIL, GOE 503 AIRFOIL, GOE 514 AIRFOIL, AH 94-W-301. The GOE 165 (MVA MK.11) AIRFOIL is another reference profile frequently considered alongside it.