Airfoil Data
NACA661212
NACA 66(1)-212
Wing Geometry Simulator
The NACA 66(1)-212 is a thin 7.1% chord-thickness airfoil with a maximum camber of 3.5% at 45% 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 -3.5°.
Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 55 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 NACA661212 appears in the wing design of at least 18 documented aircraft, including designs from North American and Republic. Its proven track record across conventional and rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the NACA661212 typically compare it against profiles of similar thickness: E63 (4.25%), GOE 393 AIRFOIL, FX LIII-142 K 25 AIRFOIL, NACA 64(1)-212 MOD B, S4110. The NACA M4 AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the NACA661212 Airfoil
North American Aviation NA-105 Mustang V | North American | NACA 66-(1.8)15.5 | NACA 66-(1.8)12 |
North American Aviation NA-105 Mustang VI | North American | NACA 66-(1.8)15.5 | NACA 66-(1.8)12 |
North American Aviation NA-105 XP-51F | North American | NACA 66-(1.8)15.5 | NACA 66-(1.8)12 |
North American Aviation NA-105 XP-51G | North American | NACA 66-(1.8)15.5 | NACA 66-(1.8)12 |
North American Aviation NA-105 XP-51J | North American | NACA 66-(1.8)15.5 | NACA 66-(1.8)12 |
North American Aviation NA-117 P-51H Mustang | North American | NACA 66-(1.8)15.5 | NACA 66-(1.8)12 |
North American Aviation NA-120 XP-82 Twin Mustang | North American | NACA 66-(1.8)15.5 | NACA 66-(1.8)12 |
North American Aviation NA-123 P-82B Twin Mustang | North American | NACA 66-(1.8)15.5 | NACA 66-(1.8)12 |
North American Aviation NA-123 P-82C Twin Mustang | North American | NACA 66-(1.8)15.5 | NACA 66-(1.8)12 |
North American Aviation NA-123 P-82D Twin Mustang | North American | NACA 66-(1.8)15.5 | NACA 66-(1.8)12 |
North American Aviation NA-126 P-51H Mustang | North American | NACA 66-(1.8)15.5 | NACA 66-(1.8)12 |
North American Aviation NA-139 P-51H Mustang | North American | NACA 66-(1.8)15.5 | NACA 66-(1.8)12 |
North American Aviation NA-144 F-82E Twin Mustang | North American | NACA 66-(1.8)15.5 | NACA 66-(1.8)12 |
North American Aviation NA-149 F-82F Twin Mustang | North American | NACA 66-(1.8)15.5 | NACA 66-(1.8)12 |
North American Aviation NA-150 F-82G Twin Mustang | North American | NACA 66-(1.8)15.5 | NACA 66-(1.8)12 |
North American Aviation NA-150 F-82H Twin Mustang | North American | NACA 66-(1.8)15.5 | NACA 66-(1.8)12 |
Republic XP-47F Thunderbolt | Republic | NACA 66(215)-1(16.5) | NACA 67(115)-213 |
Snow S-2C | Snow | NACA 6612 mod | Constant |
Wing lofting: 17 of these aircraft taper from NACA661212 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 NACA661212 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (7.1%) and max camber (3.5%).