Airfoil Data
GOE614

The GOE 614 AIRFOIL is a thick 15.2% chord-thickness airfoil with a maximum camber of 7.6% at 29% 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 -7.6°.

Thin airfoil theory predicts a stall angle near 10.5° and a peak lift-to-drag ratio around 73 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 GOE614 typically compare it against profiles of similar thickness: MH 112 16.2%, GOE 441 AIRFOIL, Griffith 30% Suction Airfoil, GOE 228 (MVA H.38) AIRFOIL, GOE 386 AIRFOIL. The NASA SC(2)-0612 AIRFOIL is another reference profile frequently considered alongside it.