Airfoil Data
GOE420

The GOE 420 AIRFOIL is a 13.1% 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 GOE420 appears in the wing design of at least 5 documented aircraft, including designs from Baumer and DFS. 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 GOE420 typically compare it against profiles of similar thickness: FX 84-W-175, FX 75-193, GOE 16K AIRFOIL, WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA), GOE 225 (MVA H.35) AIRFOIL. The FX 38-153 AIRFOIL is another reference profile frequently considered alongside it.