Airfoil Data
GOE424

The GOE 424 AIRFOIL is a 14.7% chord-thickness airfoil with a maximum camber of 7.4% 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 -7.4°.

Thin airfoil theory predicts a stall angle near 10.6° 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 15% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

The GOE424 appears in the wing design of at least 3 documented aircraft, including designs from Fairey and Albert. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the GOE424 typically compare it against profiles of similar thickness: FX 83-W-227, IST-MT1-21, DEFIANT CANARD BL20 AIRFOIL, GOE 242 (MVA PR.2) AIRFOIL, GOE 422 AIRFOIL. The FX 66-S-196 AIRFOIL is another reference profile frequently considered alongside it.