# NACA 4418 airfoil

> What is the exact shape of the NACA 4418 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-4418-airfoil/ · JSON: https://xemstudio.com/api/geometry?object=naca-4418-airfoil · Plain text: https://xemstudio.com/objects/naca-4418-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 | 17.98 |

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

## Notes

- NACA 4418: 4 % camber at 40 % chord, 18 % 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 | 0.710 | 3.035 | 1.790 | -2.543 |
| 2.5 | 1.777 | 4.339 | 3.223 | -3.371 |
| 5 | 4.081 | 6.190 | 5.919 | -4.315 |
| 7.5 | 6.490 | 7.578 | 8.510 | -4.859 |
| 10 | 8.958 | 8.696 | 11.042 | -5.196 |
| 15 | 14.006 | 10.393 | 15.994 | -5.518 |
| 20 | 19.144 | 11.563 | 20.856 | -5.563 |
| 25 | 24.334 | 12.324 | 25.666 | -5.449 |
| 30 | 29.551 | 12.740 | 30.449 | -5.240 |
| 40 | 40.000 | 12.700 | 40.000 | -4.700 |
| 50 | 50.176 | 11.816 | 49.824 | -4.038 |
| 60 | 60.303 | 10.369 | 59.697 | -3.258 |
| 70 | 70.363 | 8.438 | 69.637 | -2.438 |
| 80 | 80.342 | 6.064 | 79.658 | -1.620 |
| 90 | 90.226 | 3.257 | 89.774 | -0.813 |
| 95 | 95.128 | 1.687 | 94.872 | -0.409 |
| 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-4418-airfoil/index.json · license: https://xemstudio.com/files/hardware/naca-4418-airfoil/LICENSE.md

- naca-4418-airfoil-section-100mm-chord: [STEP](https://xemstudio.com/files/hardware/naca-4418-airfoil/naca-4418-airfoil-section-100mm-chord.step) · [STL](https://xemstudio.com/files/hardware/naca-4418-airfoil/naca-4418-airfoil-section-100mm-chord.stl) — NACA 4418 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 4418?**

Maximum thickness 17.98 % of chord at 30.3 % chord: 17.98 mm on a 100 mm chord.

**Where is the NACA 4418's camber?**

Maximum camber 4.00 % 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 4409 airfoil](https://xemstudio.com/objects/naca-4409-airfoil/)
- [NACA 4412 airfoil](https://xemstudio.com/objects/naca-4412-airfoil/)
- [NACA 4415 airfoil](https://xemstudio.com/objects/naca-4415-airfoil/)
- [NACA 4421 airfoil](https://xemstudio.com/objects/naca-4421-airfoil/)
- [NACA 4424 airfoil](https://xemstudio.com/objects/naca-4424-airfoil/)