# Selig S4083 airfoil

> What is the exact shape of the Selig S4083 airfoil?

- Category: Airfoils › Other airfoils
- Kind: Standard part
- Basis: Coordinates from the UIUC Airfoil Coordinates Database; thickness, camber and section by Xem Studio
- Page: https://xemstudio.com/objects/s4083-airfoil/ · JSON: https://xemstudio.com/api/geometry?object=s4083-airfoil · Plain text: https://xemstudio.com/objects/s4083-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 | 8.0 |

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

## Notes

- Selig S4083: Michael Selig (S series). Maximum thickness 8.00 % of chord at 22.6 % chord; maximum camber 3.45 % of chord at 35.5 % chord.
- Coordinates from the UIUC Airfoil Coordinates Database (M. Selig, UIUC Applied Aerodynamics Group), file s4083.dat, titled 'S4083 (8%)'. 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 | 8.00 % chord at 22.6 % chord | computed from the UIUC coordinates |
| Max camber | 3.45 % chord at 35.5 % chord | computed from the UIUC coordinates |
| Published points | 81 (43 upper, 39 lower, shared leading edge) | UIUC coordinates |
| Trailing edge as published | sharp (closed) | UIUC coordinates |
| y at x = 1.25 % chord | upper +1.629 / lower -0.826 % chord | linear between the published points (UIUC coordinates) |
| y at x = 2.5 % chord | upper +2.493 / lower -1.030 % chord | linear between the published points (UIUC coordinates) |
| y at x = 5 % chord | upper +3.743 / lower -1.205 % chord | linear between the published points (UIUC coordinates) |
| y at x = 7.5 % chord | upper +4.653 / lower -1.265 % chord | linear between the published points (UIUC coordinates) |
| y at x = 10 % chord | upper +5.363 / lower -1.256 % chord | linear between the published points (UIUC coordinates) |
| y at x = 15 % chord | upper +6.356 / lower -1.142 % chord | linear between the published points (UIUC coordinates) |
| y at x = 20 % chord | upper +6.963 / lower -0.956 % chord | linear between the published points (UIUC coordinates) |
| y at x = 25 % chord | upper +7.253 / lower -0.742 % chord | linear between the published points (UIUC coordinates) |
| y at x = 30 % chord | upper +7.307 / lower -0.514 % chord | linear between the published points (UIUC coordinates) |
| y at x = 40 % chord | upper +6.941 / lower -0.066 % chord | linear between the published points (UIUC coordinates) |
| y at x = 50 % chord | upper +6.223 / lower +0.327 % chord | linear between the published points (UIUC coordinates) |
| y at x = 60 % chord | upper +5.325 / lower +0.647 % chord | linear between the published points (UIUC coordinates) |
| y at x = 70 % chord | upper +4.318 / lower +0.825 % chord | linear between the published points (UIUC coordinates) |
| y at x = 80 % chord | upper +3.196 / lower +0.720 % chord | linear between the published points (UIUC coordinates) |
| y at x = 90 % chord | upper +1.907 / lower +0.412 % chord | linear between the published points (UIUC coordinates) |
| y at x = 95 % chord | upper +1.139 / lower +0.202 % chord | linear between the published points (UIUC coordinates) |
| Coordinates source | UIUC Airfoil Coordinates Database: s4083.dat ('S4083 (8%)') | UIUC Applied Aerodynamics Group (M. Selig) |

## Where the files are

- UIUC Applied Aerodynamics Group (M. Selig): [UIUC Airfoil Coordinates Database: s4083.dat ('S4083 (8%)')](https://m-selig.ae.illinois.edu/ads/coord/s4083.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: Michael Selig (S series))](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/s4083-airfoil/index.json · license: https://xemstudio.com/files/hardware/s4083-airfoil/LICENSE.md

- s4083-airfoil-section-100mm-chord: [STEP](https://xemstudio.com/files/hardware/s4083-airfoil/s4083-airfoil-section-100mm-chord.step) · [STL](https://xemstudio.com/files/hardware/s4083-airfoil/s4083-airfoil-section-100mm-chord.stl) — Selig S4083 section, 100 mm chord × 20 mm span, 80 points from the published coordinates, single trailing-edge point (scale to your chord)

## Questions

**How thick is the Selig S4083?**

Maximum thickness 8.00 % of chord at 22.6 % chord: 8.00 mm on a 100 mm chord (computed from the UIUC coordinates).

**How much camber does the Selig S4083 have?**

Maximum camber 3.45 % of chord at 35.5 % 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.

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