Airfoil Data
GOE255

The GOE 255 (MVA CA.6) AIRFOIL is a 13.9% chord-thickness airfoil with a maximum camber of 6.9% 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 -6.9°.

Thin airfoil theory predicts a stall angle near 10.9° and a peak lift-to-drag ratio around 71 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 14% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the GOE255 typically compare it against profiles of similar thickness: NACA 2424, EPPLER 422 AIRFOIL, S1223 RTL, LIEBECK LA5055 AIRFOIL, FX 76-MP-160. The MH 60 10.08% is another reference profile frequently considered alongside it.