Airfoil Data
M12
NACA M12 AIRFOIL
Wing Geometry Simulator
The NACA M12 AIRFOIL is a 8.0% chord-thickness airfoil with a maximum camber of 4.0% at 30% 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 -4.0°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 58 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 M12 appears in the wing design of at least 1 documented aircraft — notably by Jacobs. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the M12 typically compare it against profiles of similar thickness: OAF102 AIRFOIL, CAL1215j, GOE 442 AIRFOIL, GOE 396 AIRFOIL, GOE 408 AIRFOIL. The NACA 63-212 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the M12 Airfoil
Jacobs Schweyer Weihe (TG-19) | Jacobs | Goettingen 549 | M 12 |
Wing lofting: 1 of these aircraft taper from M12 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 M12 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (8.0%) and max camber (4.0%).