NACA 23012 Airfoil
The NACA 23012 is one of the most successful airfoils ever designed — a 5-digit section, 12% thick, with its camber pushed well forward to 15% of the chord. That forward camber gives it a high maximum lift together with an unusually small pitching moment, which is why it flew on the Douglas DC-3, the Beechcraft Bonanza and a long list of 1930s and 1940s aircraft.
What the numbers mean
NACA 23012 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 12 are the maximum thickness as 12% of the chord.
Aerodynamic characteristics
The forward camber of the 230-series raises the maximum lift while keeping the quarter-chord pitching moment very small — the whole reason the series was developed. It makes positive lift at zero angle of attack with only a slight nose-down moment, a big structural advantage over more heavily cambered sections.
| Property | Typical value |
|---|---|
| Zero-lift angle α₀ | ≈ -1.1° |
| Lift coefficient at 0° | ≈ 0.12 |
| 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
- Classic airliners and transports — most famously the Douglas DC-3.
- General-aviation aircraft — the Beechcraft Bonanza and many light aircraft.
- WWII-era aircraft — widely used for its high lift and low moment.
- Wings needing low pitching moment — where trim drag and structural twist matter.
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 |
| 0.019 | +0.0318 | 0.030 | -0.0187 |
| 0.092 | +0.0627 | 0.099 | -0.0292 |
| 0.226 | +0.0757 | 0.223 | -0.0414 |
| 0.390 | +0.0719 | 0.387 | -0.0449 |
| 0.546 | +0.0598 | 0.544 | -0.0397 |
| 0.718 | +0.0409 | 0.716 | -0.0284 |
| 0.846 | +0.0238 | 0.845 | -0.0170 |
| 0.929 | +0.0114 | 0.929 | -0.0083 |
| 0.982 | +0.0030 | 0.982 | -0.0022 |
| 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 23012 is a NACA 5-digit airfoil with a design lift coefficient of 0.3, maximum camber at 15% of the chord, and 12% maximum thickness. It is famous for high lift with a very low pitching moment and flew on the DC-3 and many other aircraft.
In a 5-digit code the first digit times 0.15 gives the design lift coefficient (2 → 0.3), the next two digits are twice the position of maximum camber (30 → 15% of the chord), and the last two digits are the thickness (12%). The middle zero means it is the standard, non-reflexed camber line.
Pushing the maximum camber forward to 15% chord concentrates the lift near the nose, which keeps the quarter-chord pitching moment small — the defining advantage of the 230-series.
The Douglas DC-3 is the most famous, along with the Beechcraft Bonanza and many 1930s-1940s light aircraft, trainers and transports.