Airfoil Data
GOE550
GOE 550 AIRFOIL
Wing Geometry Simulator
The GOE 550 AIRFOIL is a 10.1% chord-thickness airfoil with a maximum camber of 5.0% at 40% 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 -5.0°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 64 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 10% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The GOE550 appears in the wing design of at least 2 documented aircraft — notably by Doppelraab. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the GOE550 typically compare it against profiles of similar thickness: MRC-16, EPPLER 598 AIRFOIL, GOE 574 AIRFOIL, NACA 65(3)-218, GOE 7K AIRFOIL. The EPPLER 338 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the GOE550 Airfoil
Doppelraab 7 | Doppelraab | Goettingen 550 | Constant |
Doppelraab IV | Doppelraab | Goettingen 550 | Constant |
Design wings in your spreadsheet
AeroSheet loads GOE550 airfoils directly into Google Sheets. Polars, 3D splines, Fusion 360 export, without leaving your spreadsheet.
Install in Google Sheets coming soonRelated Airfoils
Engineers evaluating the GOE550 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.1%) and max camber (5.0%).
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