Airfoil Data
GOE702
GOE 702 AIRFOIL
Wing Geometry Simulator
The GOE 702 AIRFOIL is a 13.3% chord-thickness airfoil with a maximum camber of 6.6% at 29% chord, suited to high-lift UAV wings, RC sailplanes, and low-Reynolds-number slow-flyers. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -6.6°.
Thin airfoil theory predicts a stall angle near 11.2° and a peak lift-to-drag ratio around 71 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 13% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the GOE702 typically compare it against profiles of similar thickness: GOE 535 AIRFOIL, GOE 502 AIRFOIL, WORTMANN FX 057-816, GOE 562 AIRFOIL, DOUGLAS LA203A AIRFOIL. The HAWKER TEMPEST 61% SEMISPAN AIRFOIL is another reference profile frequently considered alongside it.
Stop copying .dat files.
AeroSheet loads GOE702 directly into Google Sheets. Polars, 3D splines, Fusion 360 export, without leaving your spreadsheet.
Related Airfoils
Engineers evaluating the GOE702 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (13.3%) and max camber (6.6%).
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.