NACA 2412 Airfoil
The NACA 2412 is a classic general-aviation airfoil: 12% thick, with 2% camber at 40% of the chord. That modest camber lets it make useful lift even at zero angle of attack while staying gentle and predictable near the stall. It is best known as the wing section of the Cessna 172.
What the numbers mean
In the code 2412, the first digit 2 is the maximum camber as 2% of the chord, the second digit 4 is the position of that maximum camber at 40% of the chord back from the leading edge, and the last two digits 12 are the maximum thickness as 12% of the chord.
Aerodynamic characteristics
The 2% of camber shifts the whole lift curve upward compared with a symmetric section: the 2412 already makes positive lift at zero angle of attack, and reaches a slightly higher maximum lift than the 0012. The trade-off is a small nose-down pitching moment that a symmetric airfoil doesn't have.
| Property | Typical value |
|---|---|
| Zero-lift angle α₀ | ≈ −2.1° |
| Lift coefficient at 0° | ≈ 0.25 |
| Lift-curve slope | ≈ 0.105 /deg |
| Max lift coefficient Cl,max | ≈ 1.6–1.7 |
| Stall angle | ≈ 16° |
| Pitching moment Cm,c/4 | ≈ −0.05 |
Conditions: Reynolds number Re = 1×10⁶, low speed (Mach ≤ 0.15), smooth surface. Values are representative figures from thin-airfoil theory and published XFoil / wind-tunnel data, rounded for reference.
Where it's used
- Light general-aviation aircraft — most famously the Cessna 172, the most-produced aircraft in history, plus many similar light aircraft.
- Trainers — its gentle, predictable stall makes it forgiving for student pilots.
- RC models and UAVs — a dependable all-round section for model and small unmanned aircraft.
- Homebuilt and kit aircraft — a well-understood, well-documented choice.
Coordinates
Surface coordinates as fractions of the chord (x/c, y/c), generated from the standard NACA 4-digit equations with a closed trailing edge. For the full high-resolution coordinate file, use the DAT export inside the explorer.
| x/c (upper) | y/c (upper) | x/c (lower) | y/c (lower) |
|---|---|---|---|
| 0.000 | +0.0000 | 0.000 | +0.0000 |
| 0.022 | +0.0282 | 0.027 | -0.0234 |
| 0.092 | +0.0543 | 0.099 | -0.0375 |
| 0.203 | +0.0729 | 0.209 | -0.0423 |
| 0.345 | +0.0792 | 0.346 | -0.0399 |
| 0.501 | +0.0723 | 0.499 | -0.0334 |
| 0.656 | +0.0571 | 0.653 | -0.0243 |
| 0.795 | +0.0378 | 0.793 | -0.0150 |
| 0.905 | +0.0189 | 0.904 | -0.0072 |
| 0.976 | +0.0051 | 0.975 | -0.0019 |
| 1.000 | -0.0000 | 1.000 | +0.0000 |
Explore NACA 2412 in the interactive tool →
See the 3D wing, live Cl / Cd / L-D polar charts, and change the airfoil, angle of attack and Reynolds number in real time.
Open the explorer →Frequently asked questions
NACA 2412 is a cambered airfoil from the NACA 4-digit family with 2% camber at 40% chord and 12% maximum thickness. It is a classic general-aviation section, best known as the wing of the Cessna 172.
The 2 is 2% maximum camber, the 4 is the camber's position at 40% of the chord, and the 12 is 12% maximum thickness — all measured relative to the chord length.
Its most famous user is the Cessna 172, and it or close relatives appear on many light aircraft, trainers and homebuilts because of its gentle stall and good all-round performance.
Around minus 2 degrees. Because it is cambered, it still produces positive lift at 0 degrees angle of attack and only reaches zero lift when pitched down to roughly minus 2.1 degrees.
Both are 12% thick, but the 0012 is symmetric (no camber) and the 2412 has 2% camber. The 2412 makes more lift at a given angle and lifts at zero angle of attack, while the 0012 makes no lift at zero angle and has no pitching moment.