Airfoil Data
NACA632615
NACA 63(2)-615
Wing Geometry Simulator
The NACA 63(2)-615 is a 10.6% chord-thickness airfoil with a maximum camber of 5.3% at 40% 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 -5.3°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 65 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the NACA632615 typically compare it against profiles of similar thickness: I.S.A. 962, EPPLER 1213 AIRFOIL, EPPLER EC 86(-3)-914 AIRFOIL, GOE 329 (PFALZ 58) AIRFOIL, SPICA 11.73% smoothed. The NACA M23 AIRFOIL is another reference profile frequently considered alongside it.
Design wings in your spreadsheet
AeroSheet loads NACA632615 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 NACA632615 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.6%) and max camber (5.3%).
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.