Airfoil Data
M27
NACA M27 AIRFOIL
Wing Geometry Simulator
The NACA M27 AIRFOIL is a 14.3% chord-thickness airfoil with a maximum camber of 7.2% at 30% 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 -7.2°.
Thin airfoil theory predicts a stall angle near 10.8° and a peak lift-to-drag ratio around 72 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 14% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the M27 typically compare it against profiles of similar thickness: GOE 223 (MVA H.34) AIRFOIL, NACA 5-H-20 AIRFOIL, GOE 604 AIRFOIL, NACA 4421, GOE 735 AIRFOIL. The NACA 63-212 AIRFOIL is another reference profile frequently considered alongside it.
Stop copying .dat files.
AeroSheet loads M27 directly into Google Sheets. Polars, 3D splines, Fusion 360 export, without leaving your spreadsheet.
Related Airfoils
Engineers evaluating the M27 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (14.3%) and max camber (7.2%).
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.