NACA 4415 Airfoil
The NACA 4415 is a high-lift general-purpose airfoil: 15% thick, with a generous 4% camber at 40% of the chord. The combination of strong camber and real thickness gives it a high maximum lift and plenty of structural depth, which makes it a staple for light aircraft, UAVs and wind-turbine blades.
What the numbers mean
In the code 4415, the first digit 4 is the maximum camber as 4% 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 4% camber shifts the lift curve well up, so the section makes strong positive lift at zero angle of attack, together with a noticeable nose-down pitching moment. The 15% thickness supports a high maximum lift and gentle stall; the trade-off is more drag and a larger moment than low-camber sections.
| Property | Typical value |
|---|---|
| Zero-lift angle α₀ | ≈ -4.2° |
| Lift coefficient at 0° | ≈ 0.48 |
| Lift-curve slope | ≈ 0.11 /deg |
| Max lift coefficient Cl,max | ≈ 1.6–1.7 |
| Stall angle | ≈ 15–16° |
| Pitching moment Cm,c/4 | ≈ -0.11 |
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
- Wind-turbine blades — high lift plus structural thickness is ideal for blade sections.
- Light aircraft and homebuilts — strong lift and a deep, stiff wing.
- UAVs and large RC models — good lift at modest speeds.
- High-lift general-purpose use — where maximum lift matters more than minimum drag.
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 |
| 0.018 | +0.0366 | 0.030 | -0.0271 |
| 0.087 | +0.0737 | 0.104 | -0.0401 |
| 0.218 | +0.1052 | 0.231 | -0.0406 |
| 0.388 | +0.1130 | 0.389 | -0.0330 |
| 0.547 | +0.0999 | 0.543 | -0.0245 |
| 0.720 | +0.0720 | 0.714 | -0.0144 |
| 0.848 | +0.0433 | 0.843 | -0.0074 |
| 0.931 | +0.0211 | 0.928 | -0.0033 |
| 0.982 | +0.0056 | 0.982 | -0.0008 |
| 1.000 | -0.0000 | 1.000 | +0.0000 |
Explore NACA 4415 in the interactive tool →
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Open the explorer →Frequently asked questions
NACA 4415 is a cambered NACA 4-digit airfoil with 4% camber at 40% chord and 15% maximum thickness, popular for light aircraft and wind-turbine blades because of its high lift and structural depth.
The 4 is 4% maximum camber, the 4 is the camber position at 40% of the chord, and the 15 is 15% maximum thickness.
It combines high lift with enough thickness for a stiff, strong blade, which is exactly what turbine blade sections need.
Around minus 4 degrees, because the larger 4% camber makes substantial positive lift at zero angle of attack.