Airfoil Data
GOE367
GOE 367 AIRFOIL
Wing Geometry Simulator
The GOE 367 AIRFOIL is a 12.7% chord-thickness airfoil with a maximum camber of 6.4% at 40% 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 GOE367 appears in the wing design of at least 1 documented aircraft — notably by Klemm. Its proven track record across rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the GOE367 typically compare it against profiles of similar thickness: B-29 ROOT AIRFOIL, EPPLER 583 AIRFOIL, EPPLER 604 AIRFOIL, Fage & Collins 4, AH 94-145. The GOE 155 (SSW D.1) AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the GOE367 Airfoil
Klemm L15 | Klemm | Goettingen 367 | Constant |
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Engineers evaluating the GOE367 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (12.7%) and max camber (6.4%).
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