Airfoil Data
GOE174
GOE 174 (ALBATROS 5020) AIRFOIL
Wing Geometry Simulator
The GOE 174 (ALBATROS 5020) AIRFOIL is a 9.7% chord-thickness airfoil with a maximum camber of 4.8% 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 -4.8°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 62 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The slim profile minimises pressure drag at higher speeds but leaves limited spar depth for structural integration.
Designers evaluating the GOE174 typically compare it against profiles of similar thickness: GOE 140 (MVA H.17) AIRFOIL, GOE 392 AIRFOIL, NACA 66(2)-415, GOE 479 AIRFOIL, EPPLER 555 AIRFOIL. The NACA 64-206 is another reference profile frequently considered alongside it.
Design wings in your spreadsheet
AeroSheet loads GOE174 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 GOE174 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (9.7%) and max camber (4.8%).
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.