Airfoil Data
GOE619

The GOE 619 AIRFOIL is a 10.9% chord-thickness airfoil with a maximum camber of 5.4% 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 -5.4°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 66 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the GOE619 typically compare it against profiles of similar thickness: NACA 2418, GOE 497 AIRFOIL, GOE 319 (HANSA-BRANDENBURG II) AIRFOIL, GOE 15K AIRFOIL, CLARK YM-15 AIRFOIL. The FX 60-157 AIRFOIL is another reference profile frequently considered alongside it.