Airfoil Data
GOE199

The GOE 199 (L.F.G. 5406) 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 GOE199 typically compare it against profiles of similar thickness: GOE 417 AIRFOIL, EPPLER 378 AIRFOIL, FX 63-100 AIRFOIL, GOE 188 (SCHUETTE-LANZ 3U10) AIRFOIL, Apex 16 (normalized using XFOIL date021206). The GOE 375 AIRFOIL is another reference profile frequently considered alongside it.