Airfoil Data
GOE275

The GOE 275 (DAIMLER VI) AIRFOIL is a 8.6% chord-thickness airfoil with a maximum camber of 4.3% 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 -4.3°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 59 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 GOE275 typically compare it against profiles of similar thickness: GOE 277 (DAIMLER VIII) AIRFOIL, NACA 64-215 AIRFOIL, NACA 64(2)-215, MH 200 12.97%, S4061-096-84. The FX 84-W-175 is another reference profile frequently considered alongside it.