# NACA 0010 airfoil

> What is the exact shape of the NACA 0010 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-0010-airfoil/ · JSON: https://xemstudio.com/api/geometry?object=naca-0010-airfoil · Plain text: https://xemstudio.com/objects/naca-0010-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 | 10.0 |

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

## Notes

- NACA 0010: symmetric, 10 % 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 | 1.250 | 1.578 | 1.250 | -1.578 |
| 2.5 | 2.500 | 2.179 | 2.500 | -2.179 |
| 5 | 5.000 | 2.962 | 5.000 | -2.962 |
| 7.5 | 7.500 | 3.500 | 7.500 | -3.500 |
| 10 | 10.000 | 3.902 | 10.000 | -3.902 |
| 15 | 15.000 | 4.454 | 15.000 | -4.454 |
| 20 | 20.000 | 4.781 | 20.000 | -4.781 |
| 25 | 25.000 | 4.951 | 25.000 | -4.951 |
| 30 | 30.000 | 5.001 | 30.000 | -5.001 |
| 40 | 40.000 | 4.833 | 40.000 | -4.833 |
| 50 | 50.000 | 4.405 | 50.000 | -4.405 |
| 60 | 60.000 | 3.789 | 60.000 | -3.789 |
| 70 | 70.000 | 3.028 | 70.000 | -3.028 |
| 80 | 80.000 | 2.143 | 80.000 | -2.143 |
| 90 | 90.000 | 1.138 | 90.000 | -1.138 |
| 95 | 95.000 | 0.587 | 95.000 | -0.587 |
| 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-0010-airfoil/index.json · license: https://xemstudio.com/files/hardware/naca-0010-airfoil/LICENSE.md

- naca-0010-airfoil-section-100mm-chord: [STEP](https://xemstudio.com/files/hardware/naca-0010-airfoil/naca-0010-airfoil-section-100mm-chord.step) · [STL](https://xemstudio.com/files/hardware/naca-0010-airfoil/naca-0010-airfoil-section-100mm-chord.stl) — NACA 0010 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 0010?**

Maximum thickness 10.00 % of chord at 29.9 % chord: 10.00 mm on a 100 mm chord.

**Where is the NACA 0010's camber?**

None: it is symmetric (upper and lower surfaces mirror).

**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 0006 airfoil](https://xemstudio.com/objects/naca-0006-airfoil/)
- [NACA 0008 airfoil](https://xemstudio.com/objects/naca-0008-airfoil/)
- [NACA 0009 airfoil](https://xemstudio.com/objects/naca-0009-airfoil/)
- [NACA 0012 airfoil](https://xemstudio.com/objects/naca-0012-airfoil/)
- [NACA 0015 airfoil](https://xemstudio.com/objects/naca-0015-airfoil/)
- [NACA 0018 airfoil](https://xemstudio.com/objects/naca-0018-airfoil/)