Airfoil Data
M1
NACA-M1 AIRFOIL
Wing Geometry Simulator
The NACA-M1 AIRFOIL is a thin 3.1% chord-thickness airfoil with a maximum camber of 1.5% at 30% 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 -1.5°.
Thin airfoil theory predicts a stall angle near 12.0° and a peak lift-to-drag ratio around 44 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.
The M1 appears in the wing design of at least 1 documented aircraft — notably by Aviat. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the M1 typically compare it against profiles of similar thickness: S1010 HPV airfoil, NASA SC(2)-0406 AIRFOIL, NACA 0006, NASA SC(2)-0706 AIRFOIL, NASA SC(2)-0606 AIRFOIL. The NACA 64(1)-212 MOD A is another reference profile frequently considered alongside it.
Aircraft Using the M1 Airfoil
Aviat Millenium Swift | Aviat | NASA NLF(1)-0414F/M1 | NASA NLF(1)-0414F/M1S |
Wing lofting: 1 of these aircraft taper from M1 at the root to a different tip section. Use the Tapered filter to isolate them, then click any tip airfoil link to compare geometries.
Related Airfoils
Engineers evaluating the M1 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (3.1%) and max camber (1.5%).