NACA 0009 Airfoil
The NACA 0009 is a symmetric airfoil 9% thick with no camber. It is one of the most common choices for horizontal and vertical tails, rudders and elevators, because a symmetric section behaves the same whether deflected up or down and makes no lift until it is set at an angle.
What the numbers mean
In the code 0009, the first two digits 00 mean the section is symmetric — it has no camber — and the last two digits 09 are the maximum thickness as 9% of the chord.
Aerodynamic characteristics
As a symmetric section it makes zero lift at zero angle of attack and has no quarter-chord pitching moment. The 9% thickness is a good compromise: enough depth for structure and a reasonable maximum lift, while staying thin enough for low drag on a tail surface.
| Property | Typical value |
|---|---|
| Zero-lift angle α₀ | 0° |
| Lift coefficient at 0° | 0 |
| Lift-curve slope | ≈ 0.11 /deg |
| Max lift coefficient Cl,max | ≈ 1.2–1.3 |
| Stall angle | ≈ 12–13° |
| 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
- Horizontal and vertical tails — the classic use; symmetric so the stabiliser works both ways.
- Rudders and elevators — predictable, symmetric control response.
- Aerobatic surfaces — symmetric behaviour for upright and inverted flight.
- Helicopter and model tail rotors — a dependable thin symmetric choice.
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 | +0.0194 | 0.024 | -0.0194 |
| 0.095 | +0.0345 | 0.095 | -0.0345 |
| 0.225 | +0.0439 | 0.225 | -0.0439 |
| 0.389 | +0.0438 | 0.389 | -0.0438 |
| 0.545 | +0.0373 | 0.545 | -0.0373 |
| 0.717 | +0.0260 | 0.717 | -0.0260 |
| 0.846 | +0.0153 | 0.846 | -0.0153 |
| 0.929 | +0.0074 | 0.929 | -0.0074 |
| 0.982 | +0.0019 | 0.982 | -0.0019 |
| 1.000 | -0.0000 | 1.000 | +0.0000 |
Explore NACA 0009 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 0009 is a symmetric NACA 4-digit airfoil with no camber and 9% maximum thickness, used widely for tail surfaces and control surfaces.
The 00 means it is symmetric with no camber, and the 09 is the maximum thickness as 9% of the chord.
Zero degrees. Because it is symmetric it makes no lift at zero angle of attack.
A tail surface must make lift in either direction, so a symmetric section that behaves identically up and down is ideal.