# NACA 1410 airfoil

> What is the exact shape of the NACA 1410 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-1410-airfoil/ · JSON: https://xemstudio.com/api/geometry?object=naca-1410-airfoil · Plain text: https://xemstudio.com/objects/naca-1410-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 1410: 1 % camber at 40 % chord, 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 | 1.174 | 1.638 | 1.326 | -1.515 |
| 2.5 | 2.398 | 2.298 | 2.602 | -2.055 |
| 5 | 4.871 | 3.194 | 5.129 | -2.725 |
| 7.5 | 7.358 | 3.837 | 7.642 | -3.157 |
| 10 | 9.854 | 4.337 | 10.146 | -3.462 |
| 15 | 14.861 | 5.061 | 15.139 | -3.843 |
| 20 | 19.881 | 5.530 | 20.119 | -4.030 |
| 25 | 24.907 | 5.809 | 25.093 | -4.090 |
| 30 | 29.937 | 5.938 | 30.063 | -4.063 |
| 40 | 40.000 | 5.833 | 40.000 | -3.833 |
| 50 | 50.024 | 5.377 | 49.976 | -3.433 |
| 60 | 60.042 | 4.678 | 59.958 | -2.900 |
| 70 | 70.050 | 3.778 | 69.950 | -2.278 |
| 80 | 80.048 | 2.698 | 79.952 | -1.587 |
| 90 | 90.032 | 1.443 | 89.968 | -0.832 |
| 95 | 95.018 | 0.746 | 94.982 | -0.427 |
| 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-1410-airfoil/index.json · license: https://xemstudio.com/files/hardware/naca-1410-airfoil/LICENSE.md

- naca-1410-airfoil-section-100mm-chord: [STEP](https://xemstudio.com/files/hardware/naca-1410-airfoil/naca-1410-airfoil-section-100mm-chord.step) · [STL](https://xemstudio.com/files/hardware/naca-1410-airfoil/naca-1410-airfoil-section-100mm-chord.stl) — NACA 1410 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 1410?**

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

**Where is the NACA 1410's camber?**

Maximum camber 1.00 % 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.

## Fits with

- [NACA 1408 airfoil](https://xemstudio.com/objects/naca-1408-airfoil/)
- [NACA 1412 airfoil](https://xemstudio.com/objects/naca-1412-airfoil/)