NACA 0015 Airfoil
The NACA 0015 is a symmetric airfoil 15% thick. The extra thickness over a 0009 or 0012 gives it more internal structure and a higher maximum lift, which makes it a favourite for aerobatic wings, struts and vertical-axis wind-turbine blades — anywhere a symmetric section needs some depth.
What the numbers mean
In the code 0015, the first two digits 00 mean the section is symmetric — it has no camber — and the last two digits 15 are the maximum thickness as 15% of the chord.
Aerodynamic characteristics
It is symmetric, so lift is zero at zero angle of attack and there is no pitching moment. The 15% thickness raises the maximum lift and softens the stall compared with thinner symmetric sections, at the cost of a little more drag.
| Property | Typical value |
|---|---|
| Zero-lift angle α₀ | 0° |
| Lift coefficient at 0° | 0 |
| Lift-curve slope | ≈ 0.11 /deg |
| Max lift coefficient Cl,max | ≈ 1.4–1.5 |
| Stall angle | ≈ 15–16° |
| Pitching moment Cm,c/4 | 0 |
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
- Aerobatic wings — symmetric lift for identical upright and inverted performance.
- Vertical-axis wind turbines — Darrieus-type blades that see flow from both sides.
- Struts and pylons — a thick symmetric shape with room for structure.
- Thick tail surfaces — stabilisers and rudders needing extra stiffness.
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 |
| 0.024 | +0.0324 | 0.024 | -0.0324 |
| 0.095 | +0.0576 | 0.095 | -0.0576 |
| 0.225 | +0.0732 | 0.225 | -0.0732 |
| 0.389 | +0.0730 | 0.389 | -0.0730 |
| 0.545 | +0.0622 | 0.545 | -0.0622 |
| 0.717 | +0.0433 | 0.717 | -0.0433 |
| 0.846 | +0.0255 | 0.846 | -0.0255 |
| 0.929 | +0.0123 | 0.929 | -0.0123 |
| 0.982 | +0.0032 | 0.982 | -0.0032 |
| 1.000 | -0.0000 | 1.000 | +0.0000 |
Explore NACA 0015 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 0015 is a symmetric NACA 4-digit airfoil with no camber and 15% maximum thickness, used for aerobatic wings, struts and wind-turbine blades.
The 00 means symmetric (no camber) and the 15 is the maximum thickness as 15% of the chord.
Yes. Being symmetric it performs the same upright and inverted, and its thickness gives a gentle stall and structural depth.
Both are symmetric; the 0015 is thicker (15% vs 12%), giving a slightly higher maximum lift and more internal room, with marginally more drag.