Airfoil Data
GOE298
GOE 298 AIRFOIL
Wing Geometry Simulator
The GOE 298 AIRFOIL is a 10.4% chord-thickness airfoil with a maximum camber of 5.2% 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 -5.2°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 65 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 GOE298 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 GOE298 typically compare it against profiles of similar thickness: RAF-48 AIRFOIL, EPPLER 543 AIRFOIL, SG6040, GOE 238 (HANSA-BRANDENBURG) AIRFOIL, GOE 500 AIRFOIL. The GOE 397 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the GOE298 Airfoil
Fokker Dr.1 | Fokker | Goettingen 298 | Constant |
Design wings in your spreadsheet
AeroSheet loads GOE298 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 GOE298 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.4%) and max camber (5.2%).
Need a custom engineering simulator?
The 3D engine on this page is built by Veenie Aerospace. We build bespoke, browser-native digital twins, aerodynamic simulators, and AI physics tools for UAV startups and defense contractors.