# NACA 23024 airfoil

> What is the exact shape of the NACA 23024 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-23024-airfoil/ · JSON: https://xemstudio.com/api/geometry?object=naca-23024-airfoil · Plain text: https://xemstudio.com/objects/naca-23024-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 | 24.0 |

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

## Notes

- NACA 23024: 5-digit 230 mean line (design lift coefficient 0.3, camber peak at 15 % chord), 24 % 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 | 0.277 | 4.017 | 2.223 | -3.304 |
| 2.5 | 1.331 | 5.763 | 3.669 | -4.431 |
| 5 | 3.853 | 8.171 | 6.147 | -5.861 |
| 7.5 | 6.601 | 9.843 | 8.399 | -6.860 |
| 10 | 9.423 | 11.049 | 10.577 | -7.647 |
| 15 | 15.001 | 12.529 | 14.999 | -8.852 |
| 20 | 20.253 | 13.239 | 19.747 | -9.705 |
| 25 | 25.262 | 13.535 | 24.738 | -10.222 |
| 30 | 30.265 | 13.544 | 29.735 | -10.453 |
| 40 | 40.256 | 12.922 | 39.744 | -10.272 |
| 50 | 50.233 | 11.674 | 49.767 | -9.466 |
| 60 | 60.201 | 9.975 | 59.799 | -8.209 |
| 70 | 70.160 | 7.928 | 69.840 | -6.603 |
| 80 | 80.114 | 5.583 | 79.886 | -4.700 |
| 90 | 90.060 | 2.950 | 89.940 | -2.509 |
| 95 | 95.031 | 1.518 | 94.969 | -1.297 |
| 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-23024-airfoil/index.json · license: https://xemstudio.com/files/hardware/naca-23024-airfoil/LICENSE.md

- naca-23024-airfoil-section-100mm-chord: [STEP](https://xemstudio.com/files/hardware/naca-23024-airfoil/naca-23024-airfoil-section-100mm-chord.step) · [STL](https://xemstudio.com/files/hardware/naca-23024-airfoil/naca-23024-airfoil-section-100mm-chord.stl) — NACA 23024 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 23024?**

Maximum thickness 24.00 % of chord at 29.9 % chord: 24.00 mm on a 100 mm chord.

**Where is the NACA 23024'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.

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