# Göttingen 387 (GOE 387) airfoil

> What is the exact shape of the Göttingen 387 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/goe-387-airfoil/ · JSON: https://xemstudio.com/api/geometry?object=goe-387-airfoil · Plain text: https://xemstudio.com/objects/goe-387-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 | 14.85 |

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

## Notes

- Göttingen 387: Aerodynamische Versuchsanstalt Göttingen (Göttingen profile 387). Maximum thickness 14.85 % of chord at 30.0 % chord; maximum camber 5.52 % of chord at 40.0 % chord.
- Coordinates from the UIUC Airfoil Coordinates Database (M. Selig, UIUC Applied Aerodynamics Group), file goe387.dat, titled 'GOE 387 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 | 14.85 % chord at 30.0 % chord | computed from the UIUC coordinates |
| Max camber | 5.52 % chord at 40.0 % chord | computed from the UIUC coordinates |
| Published points | 33 (17 upper, 17 lower, shared leading edge) | UIUC coordinates |
| Trailing edge as published | sharp (closed) | UIUC coordinates |
| y at x = 1.25 % chord | upper +3.088 / lower -1.862 % chord | linear between the published points (UIUC coordinates) |
| y at x = 2.5 % chord | upper +4.526 / lower -2.174 % chord | linear between the published points (UIUC coordinates) |
| y at x = 5 % chord | upper +6.452 / lower -2.497 % chord | linear between the published points (UIUC coordinates) |
| y at x = 7.5 % chord | upper +7.879 / lower -2.721 % chord | linear between the published points (UIUC coordinates) |
| y at x = 10 % chord | upper +9.055 / lower -2.795 % chord | linear between the published points (UIUC coordinates) |
| y at x = 15 % chord | upper +10.658 / lower -2.743 % chord | linear between the published points (UIUC coordinates) |
| y at x = 20 % chord | upper +11.810 / lower -2.590 % chord | linear between the published points (UIUC coordinates) |
| y at x = 25 % chord | upper +12.288 / lower -2.337 % chord | linear between the published points (UIUC coordinates) |
| y at x = 30 % chord | upper +12.765 / lower -2.085 % chord | linear between the published points (UIUC coordinates) |
| y at x = 40 % chord | upper +12.620 / lower -1.580 % chord | linear between the published points (UIUC coordinates) |
| y at x = 50 % chord | upper +11.675 / lower -1.225 % chord | linear between the published points (UIUC coordinates) |
| y at x = 60 % chord | upper +9.980 / lower -0.870 % chord | linear between the published points (UIUC coordinates) |
| y at x = 70 % chord | upper +7.835 / lower -0.615 % chord | linear between the published points (UIUC coordinates) |
| y at x = 80 % chord | upper +5.390 / lower -0.460 % chord | linear between the published points (UIUC coordinates) |
| y at x = 90 % chord | upper +2.795 / lower -0.305 % chord | linear between the published points (UIUC coordinates) |
| y at x = 95 % chord | upper +1.447 / lower -0.252 % chord | linear between the published points (UIUC coordinates) |
| Coordinates source | UIUC Airfoil Coordinates Database: goe387.dat ('GOE 387 AIRFOIL') | UIUC Applied Aerodynamics Group (M. Selig) |

## Where the files are

- UIUC Applied Aerodynamics Group (M. Selig): [UIUC Airfoil Coordinates Database: goe387.dat ('GOE 387 AIRFOIL')](https://m-selig.ae.illinois.edu/ads/coord/goe387.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: Aerodynamische Versuchsanstalt Göttingen (Göttingen profile 387))](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/goe-387-airfoil/index.json · license: https://xemstudio.com/files/hardware/goe-387-airfoil/LICENSE.md

- goe-387-airfoil-section-100mm-chord: [STEP](https://xemstudio.com/files/hardware/goe-387-airfoil/goe-387-airfoil-section-100mm-chord.step) · [STL](https://xemstudio.com/files/hardware/goe-387-airfoil/goe-387-airfoil-section-100mm-chord.stl) — Göttingen 387 section, 100 mm chord × 20 mm span, 32 points from the published coordinates, single trailing-edge point (scale to your chord)

## Questions

**How thick is the Göttingen 387?**

Maximum thickness 14.85 % of chord at 30.0 % chord: 14.85 mm on a 100 mm chord (computed from the UIUC coordinates).

**How much camber does the Göttingen 387 have?**

Maximum camber 5.52 % of chord at 40.0 % 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

- [Clark Y airfoil](https://xemstudio.com/objects/clark-y-airfoil/)
- [Eppler E387 airfoil](https://xemstudio.com/objects/eppler-e387-airfoil/)
- [MH 32 airfoil](https://xemstudio.com/objects/mh32-airfoil/)
- [AG35 airfoil (Drela AG series)](https://xemstudio.com/objects/ag35-airfoil/)
- [Selig S7075 airfoil](https://xemstudio.com/objects/s7075-airfoil/)
- [SD7037 airfoil](https://xemstudio.com/objects/sd7037-airfoil/)
- [NACA 2412 airfoil](https://xemstudio.com/objects/naca-2412-airfoil/)
- [NACA 0012 airfoil](https://xemstudio.com/objects/naca-0012-airfoil/)