NACA 2410 Airfoil
The NACA 2410 is a slim general-aviation airfoil: 10% thick, with 2% camber at 40% of the chord. It is essentially a thinner cousin of the 2412 — a little less maximum lift and internal room, but lower drag — which suits lighter and faster light aircraft and sport designs.
What the numbers mean
In the code 2410, 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 10 are the maximum thickness as 10% of the chord.
Aerodynamic characteristics
The 2% camber lifts the whole curve so the section makes positive lift at zero angle of attack, with a small nose-down pitching moment. At 10% thickness it has slightly less maximum lift than the 12%-thick 2412 but a little less drag, making it a clean, efficient choice.
| Property | Typical value |
|---|---|
| Zero-lift angle α₀ | ≈ -2.1° |
| Lift coefficient at 0° | ≈ 0.23 |
| Lift-curve slope | ≈ 0.11 /deg |
| Max lift coefficient Cl,max | ≈ 1.5 |
| Stall angle | ≈ 14–15° |
| 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 and sport aircraft — a slimmer, lower-drag alternative to the 2412.
- Fast light wings — where reduced thickness helps cruise speed.
- RC models and UAVs — a dependable low-camber all-rounder.
- Homebuilt and kit aircraft — a well-behaved, well-documented section.
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 |
| 0.022 | +0.0239 | 0.026 | -0.0191 |
| 0.093 | +0.0467 | 0.098 | -0.0299 |
| 0.222 | +0.0649 | 0.227 | -0.0326 |
| 0.389 | +0.0687 | 0.389 | -0.0287 |
| 0.545 | +0.0603 | 0.544 | -0.0227 |
| 0.718 | +0.0433 | 0.716 | -0.0144 |
| 0.846 | +0.0260 | 0.845 | -0.0080 |
| 0.930 | +0.0126 | 0.929 | -0.0037 |
| 0.982 | +0.0033 | 0.982 | -0.0010 |
| 1.000 | -0.0000 | 1.000 | +0.0000 |
Explore NACA 2410 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 2410 is a cambered NACA 4-digit airfoil with 2% camber at 40% chord and 10% maximum thickness — a slimmer relative of the classic 2412.
The 2 is 2% maximum camber, the 4 is the camber position at 40% of the chord, and the 10 is 10% maximum thickness.
Same camber and camber position, but 2410 is thinner (10% vs 12%). It gives slightly less maximum lift and internal volume, with a little less drag.
About minus 2 degrees, because the 2% camber makes positive lift at zero angle of attack.