Airfoil Data
GOE535

The GOE 535 AIRFOIL is a 13.2% chord-thickness airfoil with a maximum camber of 6.6% at 30% 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 -6.6°.

Thin airfoil theory predicts a stall angle near 11.2° and a peak lift-to-drag ratio around 70 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 13% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

The GOE535 appears in the wing design of at least 90 documented aircraft, including designs from Akaflieg and Slingsby. Its proven track record across conventional and rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the GOE535 typically compare it against profiles of similar thickness: GOE 702 AIRFOIL, WORTMANN FX 057-816, DOUGLAS LA203A AIRFOIL, GOE 502 AIRFOIL, GOE 624 AIRFOIL. The HQ 3.0/13 AIRFOIL is another reference profile frequently considered alongside it.