Airfoil Data
GOE118

The GOE 118 (MVA MK.7) AIRFOIL is a 9.9% chord-thickness airfoil with a maximum camber of 5.0% 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 -5.0°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 63 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 GOE118 typically compare it against profiles of similar thickness: GOE 176 (ALBATROS 7020) AIRFOIL, GOE 92 AIRFOIL, EPPLER 541 AIRFOIL, EPPLER 341 AIRFOIL, LISSAMAN 7769 AIRFOIL. The E224 (10.17%) is another reference profile frequently considered alongside it.