NACA 23015 Airfoil
The NACA 23015 is the 15%-thick member of the 230-series: the same forward camber and low pitching moment as the 23012, but with more thickness for structure. It is a common wing-root and light-aircraft section where a strong, deep wing is wanted without giving up the series' high lift.
What the numbers mean
NACA 23015 is a 5-digit section. The first digit 2 times 0.15 is the design lift coefficient (0.3); the next two digits 30 are twice the position of maximum camber, placing it at 15% of the chord; the middle 0 marks the standard, non-reflexed camber line; and the last two digits 15 are the maximum thickness as 15% of the chord.
Aerodynamic characteristics
Like the rest of the 230-series it combines high maximum lift with a small pitching moment thanks to the forward camber. The 15% thickness adds structural depth and a slightly higher maximum lift than the 23012, at a little more drag.
| Property | Typical value |
|---|---|
| Zero-lift angle α₀ | ≈ -1.1° |
| Lift coefficient at 0° | ≈ 0.13 |
| Lift-curve slope | ≈ 0.11 /deg |
| Max lift coefficient Cl,max | ≈ 1.6–1.7 |
| Stall angle | ≈ 16–18° |
| Pitching moment Cm,c/4 | ≈ -0.013 |
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
- Wing roots — blended with thinner tip sections on tapered wings.
- Light general-aviation aircraft — a strong, high-lift section.
- Transports and trainers — following the DC-3-era design practice.
- Wings needing depth and low moment — structural room without large trim loads.
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 |
| 0.017 | +0.0381 | 0.032 | -0.0250 |
| 0.092 | +0.0741 | 0.099 | -0.0407 |
| 0.226 | +0.0903 | 0.223 | -0.0561 |
| 0.390 | +0.0865 | 0.387 | -0.0595 |
| 0.546 | +0.0723 | 0.543 | -0.0522 |
| 0.718 | +0.0495 | 0.716 | -0.0370 |
| 0.846 | +0.0289 | 0.845 | -0.0221 |
| 0.929 | +0.0139 | 0.929 | -0.0107 |
| 0.982 | +0.0036 | 0.982 | -0.0028 |
| 1.000 | -0.0000 | 1.000 | +0.0000 |
Explore 4-digit airfoils in the interactive tool →
The live 3D explorer currently covers the NACA 4-digit family. Use it to orbit a 3D wing and watch live Cl / Cd polar charts as you change camber, thickness, angle of attack and Reynolds number.
Open the explorer →Frequently asked questions
NACA 23015 is a NACA 5-digit airfoil with a 0.3 design lift coefficient, maximum camber at 15% chord and 15% thickness — a thicker relative of the classic 23012.
The first digit (2) times 0.15 is the design lift coefficient 0.3, the 30 is twice the 15%-chord camber position, and the 15 is the 15% thickness; the 0 marks the standard non-reflexed camber line.
Same forward camber and low pitching moment, but 23015 is thicker (15% vs 12%), giving more structural depth and a touch more maximum lift at slightly higher drag.
Commonly as a wing-root section on tapered wings and on light aircraft that want the 230-series' high lift with a deeper, stronger wing.