Airfoil Data
EH2010
EH 2.0/10
Wing Geometry Simulator
The EH 2.0/10 is a thin 7.0% chord-thickness airfoil with a maximum camber of 3.5% at 29% chord, suited to high-speed UAVs, sailplane tip sections, and propeller blade design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -3.5°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 55 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 EH2010 typically compare it against profiles of similar thickness: NASA SC(2)-0614 AIRFOIL, P-51D TIP (BL215) AIRFOIL, NACA M13 AIRFOIL, MH 26 10.99%, NASA SC(2)-0414 AIRFOIL. The BOEING VERTOL V(1.95)3009-1.25 AIRFOIL is another reference profile frequently considered alongside it.
Stop copying .dat files.
AeroSheet loads EH2010 directly into Google Sheets. Polars, 3D splines, Fusion 360 export, without leaving your spreadsheet.
Related Airfoils
Engineers evaluating the EH2010 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (7.0%) and max camber (3.5%).
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.