# NACA 4424 airfoil

> What is the exact shape of the NACA 4424 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-4424-airfoil/ · JSON: https://xemstudio.com/api/geometry?object=naca-4424-airfoil · Plain text: https://xemstudio.com/objects/naca-4424-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 | 23.97 |

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

## Notes

- NACA 4424: 4 % camber at 40 % chord, 24 % 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 | 0.530 | 3.965 | 1.970 | -3.473 |
| 2.5 | 1.536 | 5.624 | 3.464 | -4.655 |
| 5 | 3.774 | 7.940 | 6.226 | -6.065 |
| 7.5 | 6.153 | 9.650 | 8.847 | -6.932 |
| 10 | 8.611 | 11.012 | 11.389 | -7.512 |
| 15 | 13.674 | 13.045 | 16.326 | -8.170 |
| 20 | 18.858 | 14.418 | 21.142 | -8.418 |
| 25 | 24.111 | 15.286 | 25.889 | -8.411 |
| 30 | 29.401 | 15.736 | 30.599 | -8.236 |
| 40 | 40.000 | 15.600 | 40.000 | -7.600 |
| 50 | 50.235 | 14.459 | 49.765 | -6.681 |
| 60 | 60.404 | 12.641 | 59.596 | -5.530 |
| 70 | 70.483 | 10.251 | 69.517 | -4.251 |
| 80 | 80.455 | 7.345 | 79.545 | -2.901 |
| 90 | 90.301 | 3.936 | 89.699 | -1.491 |
| 95 | 95.171 | 2.036 | 94.829 | -0.759 |
| 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-4424-airfoil/index.json · license: https://xemstudio.com/files/hardware/naca-4424-airfoil/LICENSE.md

- naca-4424-airfoil-section-100mm-chord: [STEP](https://xemstudio.com/files/hardware/naca-4424-airfoil/naca-4424-airfoil-section-100mm-chord.step) · [STL](https://xemstudio.com/files/hardware/naca-4424-airfoil/naca-4424-airfoil-section-100mm-chord.stl) — NACA 4424 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 4424?**

Maximum thickness 23.97 % of chord at 30.3 % chord: 23.97 mm on a 100 mm chord.

**Where is the NACA 4424'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 4418 airfoil](https://xemstudio.com/objects/naca-4418-airfoil/)
- [NACA 4421 airfoil](https://xemstudio.com/objects/naca-4421-airfoil/)