# SD7003 airfoil

> What is the exact shape of the SD7003 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/sd7003-airfoil/ · JSON: https://xemstudio.com/api/geometry?object=sd7003-airfoil · Plain text: https://xemstudio.com/objects/sd7003-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 | 8.51 |

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

## Notes

- SD7003: Michael Selig and John Donovan (SD series). Maximum thickness 8.51 % of chord at 24.4 % chord; maximum camber 1.46 % of chord at 33.4 % chord.
- Coordinates from the UIUC Airfoil Coordinates Database (M. Selig, UIUC Applied Aerodynamics Group), file sd7003.dat, titled 'SD7003-085-88'. 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 | 8.51 % chord at 24.4 % chord | computed from the UIUC coordinates |
| Max camber | 1.46 % chord at 33.4 % chord | computed from the UIUC coordinates |
| Published points | 61 (32 upper, 30 lower, shared leading edge) | UIUC coordinates |
| Trailing edge as published | sharp (closed) | UIUC coordinates |
| y at x = 1.25 % chord | upper +1.590 / lower -1.195 % chord | linear between the published points (UIUC coordinates) |
| y at x = 2.5 % chord | upper +2.348 / lower -1.647 % chord | linear between the published points (UIUC coordinates) |
| y at x = 5 % chord | upper +3.378 / lower -2.170 % chord | linear between the published points (UIUC coordinates) |
| y at x = 7.5 % chord | upper +4.044 / lower -2.462 % chord | linear between the published points (UIUC coordinates) |
| y at x = 10 % chord | upper +4.537 / lower -2.654 % chord | linear between the published points (UIUC coordinates) |
| y at x = 15 % chord | upper +5.154 / lower -2.843 % chord | linear between the published points (UIUC coordinates) |
| y at x = 20 % chord | upper +5.504 / lower -2.896 % chord | linear between the published points (UIUC coordinates) |
| y at x = 25 % chord | upper +5.642 / lower -2.860 % chord | linear between the published points (UIUC coordinates) |
| y at x = 30 % chord | upper +5.637 / lower -2.762 % chord | linear between the published points (UIUC coordinates) |
| y at x = 40 % chord | upper +5.330 / lower -2.448 % chord | linear between the published points (UIUC coordinates) |
| y at x = 50 % chord | upper +4.742 / lower -2.032 % chord | linear between the published points (UIUC coordinates) |
| y at x = 60 % chord | upper +3.969 / lower -1.541 % chord | linear between the published points (UIUC coordinates) |
| y at x = 70 % chord | upper +3.071 / lower -0.993 % chord | linear between the published points (UIUC coordinates) |
| y at x = 80 % chord | upper +2.104 / lower -0.459 % chord | linear between the published points (UIUC coordinates) |
| y at x = 90 % chord | upper +1.098 / lower -0.053 % chord | linear between the published points (UIUC coordinates) |
| y at x = 95 % chord | upper +0.568 / lower +0.052 % chord | linear between the published points (UIUC coordinates) |
| Coordinates source | UIUC Airfoil Coordinates Database: sd7003.dat ('SD7003-085-88') | UIUC Applied Aerodynamics Group (M. Selig) |

## Where the files are

- UIUC Applied Aerodynamics Group (M. Selig): [UIUC Airfoil Coordinates Database: sd7003.dat ('SD7003-085-88')](https://m-selig.ae.illinois.edu/ads/coord/sd7003.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 and John Donovan (SD 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/sd7003-airfoil/index.json · license: https://xemstudio.com/files/hardware/sd7003-airfoil/LICENSE.md

- sd7003-airfoil-section-100mm-chord: [STEP](https://xemstudio.com/files/hardware/sd7003-airfoil/sd7003-airfoil-section-100mm-chord.step) · [STL](https://xemstudio.com/files/hardware/sd7003-airfoil/sd7003-airfoil-section-100mm-chord.stl) — SD7003 section, 100 mm chord × 20 mm span, 60 points from the published coordinates, single trailing-edge point (scale to your chord)

## Questions

**How thick is the SD7003?**

Maximum thickness 8.51 % of chord at 24.4 % chord: 8.51 mm on a 100 mm chord (computed from the UIUC coordinates).

**How much camber does the SD7003 have?**

Maximum camber 1.46 % of chord at 33.4 % 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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