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NREL S809 airfoil
What is the exact shape of the NREL S809 airfoil? · Standard part · basis: Coordinates from NREL/SR-440-6918 Table 2; thickness, camber and section by Xem Studio
Also called: s809, nrel s809, s809 wind turbine airfoil, s809 coordinates, NREL S809 coordinates, NREL S809 dat, NREL S809 STEP, NREL S809 STL, NREL S809 profile
Exact dimensions. True size, with no printing tolerance added.
- length
- 100.0 mm
- width
- 20.0 mm
- height
- 20.96 mm
Notes
- NREL S809: D. M. Somers, for NREL (wind-turbine airfoil). Maximum thickness 20.96 % of chord at 38.2 % chord; maximum camber 0.96 % of chord at 82.3 % chord.
- Coordinates from Table 2 of D.M. Somers, 'Design and Experimental Results for the S809 Airfoil' (NREL/SR-440-6918, 1997). The table starts just after the leading edge; the chord-line origin (0, 0) is used as the leading-edge point. 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.
NREL S809 airfoil size chart
| parameter | value | source |
|---|---|---|
| Max thickness | 20.96 % chord at 38.2 % chord | computed from NREL/SR-440-6918 Table 2 |
| Max camber | 0.96 % chord at 82.3 % chord | computed from NREL/SR-440-6918 Table 2 |
| Published points | 62 (32 upper, 31 lower, shared leading edge, the (0, 0) leading edge added) | NREL/SR-440-6918 Table 2 |
| Trailing edge as published | sharp (closed) | NREL/SR-440-6918 Table 2 |
| y at x = 1.25 % chord | upper +1.787 / lower -1.475 % chord | linear between the published points (NREL/SR-440-6918 Table 2) |
| y at x = 2.5 % chord | upper +2.705 / lower -2.254 % chord | linear between the published points (NREL/SR-440-6918 Table 2) |
| y at x = 5 % chord | upper +4.069 / lower -3.492 % chord | linear between the published points (NREL/SR-440-6918 Table 2) |
| y at x = 7.5 % chord | upper +5.104 / lower -4.569 % chord | linear between the published points (NREL/SR-440-6918 Table 2) |
| y at x = 10 % chord | upper +5.951 / lower -5.544 % chord | linear between the published points (NREL/SR-440-6918 Table 2) |
| y at x = 15 % chord | upper +7.300 / lower -7.230 % chord | linear between the published points (NREL/SR-440-6918 Table 2) |
| y at x = 20 % chord | upper +8.332 / lower -8.594 % chord | linear between the published points (NREL/SR-440-6918 Table 2) |
| y at x = 25 % chord | upper +9.114 / lower -9.665 % chord | linear between the published points (NREL/SR-440-6918 Table 2) |
| y at x = 30 % chord | upper +9.651 / lower -10.434 % chord | linear between the published points (NREL/SR-440-6918 Table 2) |
| y at x = 40 % chord | upper +10.106 / lower -10.804 % chord | linear between the published points (NREL/SR-440-6918 Table 2) |
| y at x = 50 % chord | upper +9.500 / lower -9.350 % chord | linear between the published points (NREL/SR-440-6918 Table 2) |
| y at x = 60 % chord | upper +7.724 / lower -6.819 % chord | linear between the published points (NREL/SR-440-6918 Table 2) |
| y at x = 70 % chord | upper +5.771 / lower -4.232 % chord | linear between the published points (NREL/SR-440-6918 Table 2) |
| y at x = 80 % chord | upper +3.900 / lower -2.014 % chord | linear between the published points (NREL/SR-440-6918 Table 2) |
| y at x = 90 % chord | upper +2.044 / lower -0.439 % chord | linear between the published points (NREL/SR-440-6918 Table 2) |
| y at x = 95 % chord | upper +0.996 / lower -0.019 % chord | linear between the published points (NREL/SR-440-6918 Table 2) |
| Coordinates source | Design and Experimental Results for the S809 Airfoil, NREL/SR-440-6918 (1997), Table 2 (coordinates) | NREL (D.M. Somers) |
Where the files are
Other publishers' files are linked, not hosted. "verify" = check the license at the link before commercial use.
| NREL (D.M. Somers) | Design and Experimental Results for the S809 Airfoil, NREL/SR-440-6918 (1997), Table 2 (coordinates) | web | US Government-sponsored report; coordinates are facts |
Free files
★ Free files 1 parts. Xem Studio design: free to use, print and sell things from; not to be republished as files. Xem Studio Design License. index.json
| nrel-s809-airfoil-section-100mm-chord | NREL S809 section, 100 mm chord × 20 mm span, 61 points from the published coordinates, single trailing-edge point (scale to your chord) | STEP · STL |
https://xemstudio.com/mcp to Claude, ChatGPT, Cursor or any MCP client (free, no account, one minute) and it can look up exact sizes, mating fits and free STEP/STL from every chat.Plain text: sheet.txt · JSON: /api/geometry?object=nrel-s809-airfoil
Fits with
Questions
How thick is the NREL S809?
Maximum thickness 20.96 % of chord at 38.2 % chord: 20.96 mm on a 100 mm chord (computed from NREL/SR-440-6918 Table 2).
How much camber does the NREL S809 have?
Maximum camber 0.96 % of chord at 82.3 % chord (computed from NREL/SR-440-6918 Table 2).
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.