Airfoil Data
GOE504

The GOE 504 AIRFOIL is a 14.2% chord-thickness airfoil with a maximum camber of 7.1% at 39% chord, suited to high-lift UAV wings, RC sailplanes, and low-Reynolds-number slow-flyers. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -7.1°.

Thin airfoil theory predicts a stall angle near 10.8° and a peak lift-to-drag ratio around 72 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 14% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the GOE504 typically compare it against profiles of similar thickness: GOE 289 (MVA 289) AIRFOIL, GOE 744 AIRFOIL, RAF 19 AIRFOIL, GOE 447 AIRFOIL, FX 84-W-218. The EPPLER 541 AIRFOIL is another reference profile frequently considered alongside it.