Airfoil Data
GOE222

The GOE 222 (MVA H.33) AIRFOIL is a thick 15.3% chord-thickness airfoil with a maximum camber of 7.7% at 39% 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 -7.7°.

Thin airfoil theory predicts a stall angle near 10.4° 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 GOE222 typically compare it against profiles of similar thickness: LIEBECK L1003 AIRFOIL, AH 93-W-300, USA 35 A AIRFOIL, USA 35 AIRFOIL, GOE 386 AIRFOIL. The AG19 is another reference profile frequently considered alongside it.