# NACA 63-412 airfoil

> What is the exact shape of the NACA 63-412 airfoil?

- Category: Airfoils › NACA 6-series
- Kind: Standard part
- Basis: Coordinates from the UIUC Airfoil Coordinates Database; thickness, camber and section by Xem Studio
- Page: https://xemstudio.com/objects/naca-63-412-airfoil/ · JSON: https://xemstudio.com/api/geometry?object=naca-63-412-airfoil · Plain text: https://xemstudio.com/objects/naca-63-412-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 63-412: NACA 6-series (tabulated in NACA Report 824, Abbott, von Doenhoff & Stivers, 1945). Maximum thickness 12.00 % of chord at 34.9 % chord; maximum camber 2.20 % of chord at 50.0 % chord.
- Coordinates from the UIUC Airfoil Coordinates Database (M. Selig, UIUC Applied Aerodynamics Group), file n63412.dat, titled 'NACA 63-412 AIRFOIL'. Thickness and camber are computed by Xem Studio from those points (vertical distance at equal x, linear between points).
- The published trailing edge is sharp, so the section uses it as printed.
- 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

| parameter | value | source |
|---|---|---|
| Max thickness | 12.00 % chord at 34.9 % chord | computed from the UIUC coordinates |
| Max camber | 2.20 % chord at 50.0 % chord | computed from the UIUC coordinates |
| Published points | 51 (26 upper, 26 lower, shared leading edge) | UIUC coordinates |
| Trailing edge as published | sharp (closed) | UIUC coordinates |
| y at x = 1.25 % chord | upper +1.846 / lower -1.191 % chord | linear between the published points (UIUC coordinates) |
| y at x = 2.5 % chord | upper +2.567 / lower -1.636 % chord | linear between the published points (UIUC coordinates) |
| y at x = 5 % chord | upper +3.636 / lower -2.219 % chord | linear between the published points (UIUC coordinates) |
| y at x = 7.5 % chord | upper +4.456 / lower -2.639 % chord | linear between the published points (UIUC coordinates) |
| y at x = 10 % chord | upper +5.123 / lower -2.960 % chord | linear between the published points (UIUC coordinates) |
| y at x = 15 % chord | upper +6.180 / lower -3.422 % chord | linear between the published points (UIUC coordinates) |
| y at x = 20 % chord | upper +6.956 / lower -3.731 % chord | linear between the published points (UIUC coordinates) |
| y at x = 25 % chord | upper +7.514 / lower -3.912 % chord | linear between the published points (UIUC coordinates) |
| y at x = 30 % chord | upper +7.878 / lower -3.982 % chord | linear between the published points (UIUC coordinates) |
| y at x = 40 % chord | upper +8.059 / lower -3.780 % chord | linear between the published points (UIUC coordinates) |
| y at x = 50 % chord | upper +7.567 / lower -3.164 % chord | linear between the published points (UIUC coordinates) |
| y at x = 60 % chord | upper +6.568 / lower -2.273 % chord | linear between the published points (UIUC coordinates) |
| y at x = 70 % chord | upper +5.166 / lower -1.256 % chord | linear between the published points (UIUC coordinates) |
| y at x = 80 % chord | upper +3.506 / lower -0.302 % chord | linear between the published points (UIUC coordinates) |
| y at x = 90 % chord | upper +1.748 / lower +0.329 % chord | linear between the published points (UIUC coordinates) |
| y at x = 95 % chord | upper +0.885 / lower +0.328 % chord | linear between the published points (UIUC coordinates) |
| Coordinates source | UIUC Airfoil Coordinates Database: n63412.dat ('NACA 63-412 AIRFOIL') | UIUC Applied Aerodynamics Group (M. Selig) |

## Where the files are

- UIUC Applied Aerodynamics Group (M. Selig): [UIUC Airfoil Coordinates Database: n63412.dat ('NACA 63-412 AIRFOIL')](https://m-selig.ae.illinois.edu/ads/coord/n63412.dat) — web — UIUC Airfoil Coordinates Database, public research data; coordinates are facts, cited and linked, not rehosted
- UIUC Applied Aerodynamics Group (M. Selig): [UIUC Airfoil Coordinates Database (original: NACA 6-series (tabulated in NACA Report 824, Abbott, von Doenhoff & Stivers, 1945))](https://m-selig.ae.illinois.edu/ads/coord_database.html) — web — UIUC Airfoil Coordinates Database, public research data; coordinates are facts, cited and linked, not rehosted

## Free STEP/STL (1 parts, Xem Studio Design License, Xem Studio)

Index: https://xemstudio.com/files/hardware/naca-63-412-airfoil/index.json · license: https://xemstudio.com/files/hardware/naca-63-412-airfoil/LICENSE.md

- naca-63-412-airfoil-section-100mm-chord: [STEP](https://xemstudio.com/files/hardware/naca-63-412-airfoil/naca-63-412-airfoil-section-100mm-chord.step) · [STL](https://xemstudio.com/files/hardware/naca-63-412-airfoil/naca-63-412-airfoil-section-100mm-chord.stl) — NACA 63-412 section, 100 mm chord × 20 mm span, 50 points from the published coordinates, single trailing-edge point (scale to your chord)

## Questions

**How thick is the NACA 63-412?**

Maximum thickness 12.00 % of chord at 34.9 % chord: 12.00 mm on a 100 mm chord (computed from the UIUC coordinates).

**How much camber does the NACA 63-412 have?**

Maximum camber 2.20 % of chord at 50.0 % chord (computed from the UIUC coordinates).

**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 2412 airfoil](https://xemstudio.com/objects/naca-2412-airfoil/)
- [NACA 0012 airfoil](https://xemstudio.com/objects/naca-0012-airfoil/)