Airfoil Data
GOE655
GOE 655 AIRFOIL
Wing Geometry Simulator
The GOE 655 AIRFOIL is a 11.3% chord-thickness airfoil with a maximum camber of 5.6% 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 -5.6°.
Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 67 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The GOE655 appears in the wing design of at least 1 documented aircraft — notably by Messerschmitt. Its proven track record across rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the GOE655 typically compare it against profiles of similar thickness: N-10, N-11, DAI 1238, FX 84-W-140, FX 63-145 AIRFOIL. The Prandtl-D Wingtip NASA TP-2016-219072 is another reference profile frequently considered alongside it.
Aircraft Using the GOE655 Airfoil
Messerschmitt M 29 | Messerschmitt | Goettingen 655 | Constant |
Design wings in your spreadsheet
AeroSheet loads GOE655 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 GOE655 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (11.3%) and max camber (5.6%).
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