Airfoil Data
GOE418
GOE 418 AIRFOIL
Wing Geometry Simulator
The GOE 418 AIRFOIL is a 11.1% 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 GOE418 appears in the wing design of at least 1 documented aircraft — notably by Fokker. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the GOE418 typically compare it against profiles of similar thickness: NACA M9 AIRFOIL, IST-MT1-12, GOE 584 AIRFOIL, AH 93-W-145, EPPLER 549 AIRFOIL. The SG6041 is another reference profile frequently considered alongside it.
Aircraft Using the GOE418 Airfoil
Fokker D.VII | Fokker | Goettingen 418 ? | Goettingen 418 mod ? |
Wing lofting: 1 of these aircraft taper from GOE418 at the root to a different tip section. Use the Tapered filter to isolate them, then click any tip airfoil link to compare geometries.
Design wings in your spreadsheet
AeroSheet loads GOE418 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 GOE418 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (11.1%) and max camber (5.6%).
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