NACA 2415 Airfoil
The NACA 2415 is a general-aviation airfoil with the same gentle 2% camber as the 2412 but more thickness — 15% of the chord. The extra depth gives more room for spars and fuel and a slightly higher maximum lift, which is why it appears on light aircraft and homebuilts that want the familiar 2412 manners with a stronger wing.
What the numbers mean
In the code 2415, 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 15 are the maximum thickness as 15% of the chord.
Aerodynamic characteristics
The 2% camber gives positive lift at zero angle and a small nose-down moment, just like the 2412. The 15% thickness raises the maximum lift a little and gives a gentle stall, with slightly more drag than the thinner sections.
| Property | Typical value |
|---|---|
| Zero-lift angle α₀ | ≈ -2.1° |
| Lift coefficient at 0° | ≈ 0.24 |
| Lift-curve slope | ≈ 0.11 /deg |
| Max lift coefficient Cl,max | ≈ 1.6 |
| 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 — the 2412's habits with a deeper, stronger wing.
- Homebuilt and kit aircraft — extra spar depth and fuel volume.
- Trainers — gentle, predictable stall behaviour.
- UAVs and larger RC models — structural room for bigger spans.
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 |
| 0.021 | +0.0346 | 0.027 | -0.0299 |
| 0.091 | +0.0658 | 0.100 | -0.0490 |
| 0.221 | +0.0893 | 0.228 | -0.0570 |
| 0.389 | +0.0930 | 0.389 | -0.0530 |
| 0.546 | +0.0811 | 0.544 | -0.0434 |
| 0.718 | +0.0577 | 0.715 | -0.0289 |
| 0.847 | +0.0344 | 0.844 | -0.0165 |
| 0.930 | +0.0167 | 0.929 | -0.0078 |
| 0.982 | +0.0044 | 0.982 | -0.0020 |
| 1.000 | -0.0000 | 1.000 | +0.0000 |
Explore NACA 2415 in the interactive tool →
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Open the explorer →Frequently asked questions
NACA 2415 is a cambered NACA 4-digit airfoil with 2% camber at 40% chord and 15% maximum thickness — a thicker version of the classic 2412.
The 2 is 2% maximum camber, the 4 is the camber position at 40% of the chord, and the 15 is 15% maximum thickness.
Same camber and position, but 2415 is thicker (15% vs 12%), giving slightly more maximum lift and much more internal structural room, at a little more drag.
Around minus 2 degrees, since the 2% camber produces positive lift at zero angle of attack.