# NACA 23009 airfoil

> What is the exact shape of the NACA 23009 airfoil, and what do the digits mean?

- Category: Airfoils › NACA 5-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-23009-airfoil/ · JSON: https://xemstudio.com/api/geometry?object=naca-23009-airfoil · Plain text: https://xemstudio.com/objects/naca-23009-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 | 9.0 |

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

## Notes

- NACA 23009: 5-digit 230 mean line (design lift coefficient 0.3, camber peak at 15 % chord), 9 % thick.
- NACA 5-digit 230xx: '2' × 3/2 = design lift coefficient 0.3; '30' = camber peak at 15 % chord on a simple mean line; last two digits = maximum thickness in % of chord (NACA Report 610; TM-4741).
- 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 | 0.885 | 1.729 | 1.615 | -1.016 |
| 2.5 | 2.062 | 2.577 | 2.938 | -1.246 |
| 5 | 4.570 | 3.786 | 5.430 | -1.476 |
| 7.5 | 7.163 | 4.623 | 7.837 | -1.640 |
| 10 | 9.784 | 5.207 | 10.216 | -1.804 |
| 15 | 15.000 | 5.847 | 15.000 | -2.170 |
| 20 | 20.095 | 6.069 | 19.905 | -2.535 |
| 25 | 25.098 | 6.111 | 24.902 | -2.798 |
| 30 | 30.099 | 6.045 | 29.901 | -2.954 |
| 40 | 40.096 | 5.674 | 39.904 | -3.024 |
| 50 | 50.088 | 5.068 | 49.912 | -2.859 |
| 60 | 60.075 | 4.293 | 59.925 | -2.526 |
| 70 | 70.060 | 3.387 | 69.940 | -2.062 |
| 80 | 80.043 | 2.370 | 79.957 | -1.486 |
| 90 | 90.023 | 1.244 | 89.977 | -0.803 |
| 95 | 95.012 | 0.638 | 94.988 | -0.417 |
| 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-23009-airfoil/index.json · license: https://xemstudio.com/files/hardware/naca-23009-airfoil/LICENSE.md

- naca-23009-airfoil-section-100mm-chord: [STEP](https://xemstudio.com/files/hardware/naca-23009-airfoil/naca-23009-airfoil-section-100mm-chord.step) · [STL](https://xemstudio.com/files/hardware/naca-23009-airfoil/naca-23009-airfoil-section-100mm-chord.stl) — NACA 23009 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 23009?**

Maximum thickness 9.00 % of chord at 29.9 % chord: 9.00 mm on a 100 mm chord.

**Where is the NACA 23009's camber?**

Maximum camber 1.84 % of chord at 15.0 % 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.

## Fits with

- [NACA 23012 airfoil](https://xemstudio.com/objects/naca-23012-airfoil/)
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- [NACA 23018 airfoil](https://xemstudio.com/objects/naca-23018-airfoil/)
- [NACA 23021 airfoil](https://xemstudio.com/objects/naca-23021-airfoil/)
- [NACA 23024 airfoil](https://xemstudio.com/objects/naca-23024-airfoil/)