Airfoil Data
GOE601
GOE 601 AIRFOIL
Wing Geometry Simulator
The GOE 601 AIRFOIL is a 10.2% chord-thickness airfoil with a maximum camber of 5.1% at 39% 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 -5.1°.
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 GOE601 appears in the wing design of at least 1 documented aircraft — notably by Junkers. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the GOE601 typically compare it against profiles of similar thickness: GOE 460 AIRFOIL, GOE 575 AIRFOIL, EPPLER 329 AIRFOIL, EPPLER 542 AIRFOIL, SG6043. The MH 150 23.89% is another reference profile frequently considered alongside it.
Aircraft Using the GOE601 Airfoil
Junkers Ju 87 Stuka | Junkers | Goettingen 601 | Constant |
Design wings in your spreadsheet
AeroSheet loads GOE601 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 GOE601 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.2%) and max camber (5.1%).
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