Airfoil Data
GOE198

The GOE 198 (L.F.G. 5294) AIRFOIL is a 10.3% chord-thickness airfoil with a maximum camber of 5.1% at 40% 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 -5.1°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 64 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 10% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the GOE198 typically compare it against profiles of similar thickness: GOE 165 (MVA MK.11) AIRFOIL, GOE 650 AIRFOIL, AH 79-K-132/20, EPPLER 593 AIRFOIL, I.S.A. 961. The NACA 1408 is another reference profile frequently considered alongside it.