Airfoil Data
E423
E423
Wing Geometry Simulator
The E423 is a thick 15.8% chord-thickness airfoil with a maximum camber of 7.9% at 40% 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 -7.9°.
Thin airfoil theory predicts a stall angle near 10.3° and a peak lift-to-drag ratio around 74 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 16% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the E423 typically compare it against profiles of similar thickness: NACA 4424, USA 32 AIRFOIL, FX 74-Cl5-140 MOD (smoothed), GOE 382 AIRFOIL, RONCZ 1046 VOYAGER CANARD AIRFOIL. The LA2573A is another reference profile frequently considered alongside it.
Stop copying .dat files.
AeroSheet loads E423 directly into Google Sheets. Polars, 3D splines, Fusion 360 export, without leaving your spreadsheet.
Related Airfoils
Engineers evaluating the E423 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (15.8%) and max camber (7.9%).
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.