# NACA 4409 airfoil

> What is the exact shape of the NACA 4409 airfoil, and what do the digits mean?

- Category: Airfoils › NACA 4-digit
- Kind: Standard part
- Basis: Computed from the NACA equations (Report 460 / Report 610, restated in NASA TM-4741)
- Page: https://xemstudio.com/objects/naca-4409-airfoil/ · JSON: https://xemstudio.com/api/geometry?object=naca-4409-airfoil · Plain text: https://xemstudio.com/objects/naca-4409-airfoil/sheet.txt
- License: dimension sheet CC BY 4.0 (Xem Studio); files Xem Studio Design License (free to use and sell from, not to redistribute as files: https://xemstudio.com/license/)
- Use in every chat: add https://xemstudio.com/mcp as a connector (https://xemstudio.com/use-with-ai/)

## Overall (mm)

| length | width | height |
|---|---|---|
| 100.0 | 20.0 | 8.99 |

**Exact dimensions.** True size, with no printing tolerance added.

## Notes

- NACA 4409: 4 % camber at 40 % chord, 9 % thick.
- NACA 4-digit: first digit = maximum camber in % of chord, second = its position in tenths of chord, last two = maximum thickness in % of chord (NACA Report 460).
- Ordinates are in % of chord from the leading edge, computed from the published equations with the closed-trailing-edge thickness coefficient (−0.1036, as in NASA TM-4741). The original reports use an open trailing edge (−0.1015); the difference is under 0.03 % of chord near the trailing edge.
- The file is a 100 mm chord section, 20 mm deep: scale it uniformly to your chord, or import the STEP and sweep or loft it into a wing. Thickness scales with chord; the shape is the same at any size.

## Sizes

| x (% chord) | upper x | upper y | lower x | lower y |
|---|---|---|---|---|
| 0 | 0.000 | 0.000 | 0.000 | 0.000 |
| 1.25 | 0.980 | 1.641 | 1.520 | -1.148 |
| 2.5 | 2.139 | 2.412 | 2.861 | -1.443 |
| 5 | 4.540 | 3.564 | 5.460 | -1.689 |
| 7.5 | 6.995 | 4.469 | 8.005 | -1.750 |
| 10 | 9.479 | 5.223 | 10.521 | -1.723 |
| 15 | 14.503 | 6.415 | 15.497 | -1.540 |
| 20 | 19.572 | 7.282 | 20.428 | -1.282 |
| 25 | 24.667 | 7.881 | 25.333 | -1.006 |
| 30 | 29.775 | 8.245 | 30.225 | -0.745 |
| 40 | 40.000 | 8.350 | 40.000 | -0.350 |
| 50 | 50.088 | 7.853 | 49.912 | -0.075 |
| 60 | 60.151 | 6.962 | 59.849 | 0.149 |
| 70 | 70.181 | 5.719 | 69.819 | 0.281 |
| 80 | 80.171 | 4.143 | 79.829 | 0.301 |
| 90 | 90.113 | 2.240 | 89.887 | 0.205 |
| 95 | 95.064 | 1.163 | 94.936 | 0.115 |
| 100 | 100.000 | -0.000 | 100.000 | 0.000 |

## Where the files are

- NACA (NASA Technical Reports Server): [Report 460: The characteristics of 78 related airfoil sections from tests in the variable-density wind tunnel (Jacobs, Ward, Pinkerton, 1933)](https://ntrs.nasa.gov/citations/19930091108) — web — Publisher's page; dimensions are facts
- NASA: [TM-4741: Computer program to obtain ordinates for NACA airfoils (Ladson, Brooks, Hill, Sproles, 1996)](https://www.pdas.com/refs/tm4741.pdf) — web — Publisher's page; dimensions are facts

## Free STEP/STL (1 parts, Xem Studio Design License, Xem Studio)

Index: https://xemstudio.com/files/hardware/naca-4409-airfoil/index.json · license: https://xemstudio.com/files/hardware/naca-4409-airfoil/LICENSE.md

- naca-4409-airfoil-section-100mm-chord: [STEP](https://xemstudio.com/files/hardware/naca-4409-airfoil/naca-4409-airfoil-section-100mm-chord.step) · [STL](https://xemstudio.com/files/hardware/naca-4409-airfoil/naca-4409-airfoil-section-100mm-chord.stl) — NACA 4409 section, 100 mm chord × 20 mm span, closed trailing edge, 160 points from the equations (scale to your chord)

## Questions

**How thick is the NACA 4409?**

Maximum thickness 8.99 % of chord at 30.3 % chord: 8.99 mm on a 100 mm chord.

**Where is the NACA 4409's camber?**

Maximum camber 4.00 % of chord at 40.0 % chord.

**How do I use it for my wing?**

Scale the 100 mm section to your chord (e.g. 180 mm chord = 180 % scale), then extrude or loft between root and tip sections. For a tapered wing, scale a root and a tip copy and loft between them.

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