Airfoil Data
GOE387

The GOE 387 AIRFOIL is a 12.8% chord-thickness airfoil with a maximum camber of 6.4% 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 -6.4°.

Thin airfoil theory predicts a stall angle near 11.3° 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 GOE387 appears in the wing design of at least 59 documented aircraft, including designs from Fairchild and Yakovlev. 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 GOE387 typically compare it against profiles of similar thickness: NACA 4418, MH 114 13.02%, GOE 433 AIRFOIL, EPPLER 603 AIRFOIL, AH 94-145. The LOCKHEED C-141 BL113.6 AIRFOIL is another reference profile frequently considered alongside it.