Airfoil Data
GOE417

The GOE 417 AIRFOIL is a 8.8% 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 GOE417 typically compare it against profiles of similar thickness: GOE 199 (L.F.G. 5406) AIRFOIL, EPPLER 378 AIRFOIL, FX 63-100 AIRFOIL, Apex 16 (normalized using XFOIL date021206), GOE 134 (MVA H.12) AIRFOIL. The GOE 290 (MVA 290) AIRFOIL is another reference profile frequently considered alongside it.