Airfoil Data
GOE316
GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL
Wing Geometry Simulator
The GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL is a 8.8% chord-thickness airfoil with a maximum camber of 4.4% 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 -4.4°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 60 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 GOE316 typically compare it against profiles of similar thickness: DAE 41, AH-7-47-6 AIRFOIL, GOE 195 AIRFOIL, MH 116 9.84%, GOE 286 AIRFOIL. The EPPLER 521 AIRFOIL is another reference profile frequently considered alongside it.
Design wings in your spreadsheet
AeroSheet loads GOE316 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 GOE316 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.8%) and max camber (4.4%).
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.