# NACA 1412 airfoil

> What is the exact shape of the NACA 1412 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-1412-airfoil/ · JSON: https://xemstudio.com/api/geometry?object=naca-1412-airfoil · Plain text: https://xemstudio.com/objects/naca-1412-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 | 12.0 |

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

## Notes

- NACA 1412: 1 % camber at 40 % chord, 12 % 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 | 1.158 | 1.953 | 1.342 | -1.830 |
| 2.5 | 2.378 | 2.733 | 2.622 | -2.491 |
| 5 | 4.845 | 3.786 | 5.155 | -3.317 |
| 7.5 | 7.330 | 4.536 | 7.670 | -3.857 |
| 10 | 9.825 | 5.117 | 10.175 | -4.242 |
| 15 | 14.833 | 5.952 | 15.167 | -4.733 |
| 20 | 19.857 | 6.486 | 20.143 | -4.986 |
| 25 | 24.889 | 6.799 | 25.111 | -5.080 |
| 30 | 29.925 | 6.938 | 30.075 | -5.063 |
| 40 | 40.000 | 6.800 | 40.000 | -4.800 |
| 50 | 50.029 | 6.258 | 49.971 | -4.314 |
| 60 | 60.051 | 5.436 | 59.949 | -3.658 |
| 70 | 70.061 | 4.383 | 69.939 | -2.883 |
| 80 | 80.057 | 3.126 | 79.943 | -2.015 |
| 90 | 90.038 | 1.670 | 89.962 | -1.059 |
| 95 | 95.021 | 0.863 | 94.979 | -0.544 |
| 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-1412-airfoil/index.json · license: https://xemstudio.com/files/hardware/naca-1412-airfoil/LICENSE.md

- naca-1412-airfoil-section-100mm-chord: [STEP](https://xemstudio.com/files/hardware/naca-1412-airfoil/naca-1412-airfoil-section-100mm-chord.step) · [STL](https://xemstudio.com/files/hardware/naca-1412-airfoil/naca-1412-airfoil-section-100mm-chord.stl) — NACA 1412 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 1412?**

Maximum thickness 12.00 % of chord at 29.9 % chord: 12.00 mm on a 100 mm chord.

**Where is the NACA 1412'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 1410 airfoil](https://xemstudio.com/objects/naca-1410-airfoil/)