Airfoil Data
NACA654421A05
NACA 65(4)-421 a=0.5
Wing Geometry Simulator
The NACA 65(4)-421 a=0.5 is a 13.5% chord-thickness airfoil with a maximum camber of 6.7% 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 -6.7°.
Thin airfoil theory predicts a stall angle near 11.1° 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 NACA654421A05 typically compare it against profiles of similar thickness: GOE 679 AIRFOIL, FX 76-MP-120, AH 95-160, GOE 628 AIRFOIL, FX S 02-196 AIRFOIL. The NACA 63-206 is another reference profile frequently considered alongside it.
Design wings in your spreadsheet
AeroSheet loads NACA654421A05 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 NACA654421A05 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (13.5%) and max camber (6.7%).
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.