# NACA 2414 airfoil

> What is the exact shape of the NACA 2414 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-2414-airfoil/ · JSON: https://xemstudio.com/api/geometry?object=naca-2414-airfoil · Plain text: https://xemstudio.com/objects/naca-2414-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 | 14.0 |

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

## Notes

- NACA 2414: 2 % camber at 40 % chord, 14 % 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 | 1.037 | 2.322 | 1.463 | -2.076 |
| 2.5 | 2.215 | 3.279 | 2.785 | -2.795 |
| 5 | 4.639 | 4.600 | 5.361 | -3.663 |
| 7.5 | 7.103 | 5.563 | 7.897 | -4.204 |
| 10 | 9.591 | 6.323 | 10.409 | -4.573 |
| 15 | 14.611 | 7.443 | 15.389 | -5.005 |
| 20 | 19.666 | 8.185 | 20.334 | -5.185 |
| 25 | 24.740 | 8.645 | 25.260 | -5.207 |
| 30 | 29.825 | 8.874 | 30.175 | -5.124 |
| 40 | 40.000 | 8.766 | 40.000 | -4.766 |
| 50 | 50.069 | 8.111 | 49.931 | -4.222 |
| 60 | 60.118 | 7.081 | 59.882 | -3.526 |
| 70 | 70.141 | 5.737 | 69.859 | -2.737 |
| 80 | 80.133 | 4.108 | 79.867 | -1.886 |
| 90 | 90.088 | 2.201 | 89.912 | -0.979 |
| 95 | 95.050 | 1.139 | 94.950 | -0.500 |
| 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-2414-airfoil/index.json · license: https://xemstudio.com/files/hardware/naca-2414-airfoil/LICENSE.md

- naca-2414-airfoil-section-100mm-chord: [STEP](https://xemstudio.com/files/hardware/naca-2414-airfoil/naca-2414-airfoil-section-100mm-chord.step) · [STL](https://xemstudio.com/files/hardware/naca-2414-airfoil/naca-2414-airfoil-section-100mm-chord.stl) — NACA 2414 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 2414?**

Maximum thickness 14.00 % of chord at 30.0 % chord: 14.00 mm on a 100 mm chord.

**Where is the NACA 2414's camber?**

Maximum camber 2.00 % 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 2408 airfoil](https://xemstudio.com/objects/naca-2408-airfoil/)
- [NACA 2410 airfoil](https://xemstudio.com/objects/naca-2410-airfoil/)
- [NACA 2411 airfoil](https://xemstudio.com/objects/naca-2411-airfoil/)
- [NACA 2412 airfoil](https://xemstudio.com/objects/naca-2412-airfoil/)
- [NACA 2415 airfoil](https://xemstudio.com/objects/naca-2415-airfoil/)
- [NACA 2418 airfoil](https://xemstudio.com/objects/naca-2418-airfoil/)