Airfoil Data
GOE404
GOE 404 AIRFOIL
Wing Geometry Simulator
The GOE 404 AIRFOIL is a 11.6% chord-thickness airfoil with a maximum camber of 5.8% at 30% chord, suited to general-aviation and UAV wing design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -5.8°.
Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 68 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 12% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The GOE404 appears in the wing design of at least 1 documented aircraft — notably by Greif. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the GOE404 typically compare it against profiles of similar thickness: AH 93-157, AH 93-156, EPPLER E662 AIRFOIL, NACA 65(4)-221, EPPLER 559 AIRFOIL. The E168 (12.45%) is another reference profile frequently considered alongside it.
Aircraft Using the GOE404 Airfoil
Greif I | Greif | Goettingen 404 | Constant |
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Engineers evaluating the GOE404 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (11.6%) and max camber (5.8%).
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