Airfoil Data
GOE137

The GOE 137 (MVA H.15) AIRFOIL is a 8.7% chord-thickness airfoil with a maximum camber of 4.4% at 30% 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 -4.4°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 60 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The slim profile minimises pressure drag at higher speeds but leaves limited spar depth for structural integration.

Designers evaluating the GOE137 typically compare it against profiles of similar thickness: EPPLER 66 AIRFOIL, GOE 314 (HANSA-BRANDENBURG) AIRFOIL, K3311 (original), HAM-STD HS1-708 AIRFOIL, GOE 456 AIRFOIL. The E477 is another reference profile frequently considered alongside it.