Airfoil Data
GOE584

The GOE 584 AIRFOIL is a 11.1% chord-thickness airfoil with a maximum camber of 5.5% 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 -5.5°.

Thin airfoil theory predicts a stall angle near 11.6° 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 GOE584 typically compare it against profiles of similar thickness: AH 93-W-145, NACA 64(3)-418, IST-MT1-12, NACA M9 AIRFOIL, GOE 418 AIRFOIL. The GOE 242 (MVA PR.2) AIRFOIL is another reference profile frequently considered alongside it.