Xem Studiomeasured geometryLibrary › Airfoils › Other airfoils ·
HT08 airfoil (Drela tail section)
What is the exact shape of the HT08 airfoil? · Standard part · basis: Coordinates from the UIUC Airfoil Coordinates Database; thickness, camber and section by Xem Studio
Also called: ht08, ht 08, drela ht08, tail airfoil, HT08 airfoil, HT08 coordinates, HT08 dat, HT08 STEP, HT08 STL, HT08 profile
Exact dimensions. True size, with no printing tolerance added.
- length
- 100.0 mm
- width
- 20.0 mm
- height
- 5.0 mm
Notes
- HT08: Mark Drela (HT tail series). Maximum thickness 5.00 % of chord at 20.2 % chord; symmetric (no camber).
- Coordinates from the UIUC Airfoil Coordinates Database (M. Selig, UIUC Applied Aerodynamics Group), file ht08.dat, titled 'HT08'. Thickness and camber are computed by Xem Studio from those points (vertical distance at equal x, linear between points).
- The published trailing edge is open (0.347 % chord thick). As on the NACA pages, the file uses a single sharp trailing-edge point: each surface is shifted linearly from zero at the leading edge to meet at the mid point of the published trailing edge, a change of at most 0.174 % chord, at the trailing edge itself.
- 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.
HT08 airfoil size chart
| parameter | value | source |
|---|---|---|
| Max thickness | 5.00 % chord at 20.2 % chord | computed from the UIUC coordinates |
| Max camber | 0 (symmetric) | computed from the UIUC coordinates |
| Published points | 160 (80 upper, 81 lower, shared leading edge) | UIUC coordinates |
| Trailing edge as published | open, 0.347 % chord thick | UIUC coordinates |
| y at x = 1.25 % chord | upper +1.060 / lower -1.057 % chord | linear between the published points (UIUC coordinates) |
| y at x = 2.5 % chord | upper +1.421 / lower -1.419 % chord | linear between the published points (UIUC coordinates) |
| y at x = 5 % chord | upper +1.853 / lower -1.851 % chord | linear between the published points (UIUC coordinates) |
| y at x = 7.5 % chord | upper +2.110 / lower -2.107 % chord | linear between the published points (UIUC coordinates) |
| y at x = 10 % chord | upper +2.275 / lower -2.272 % chord | linear between the published points (UIUC coordinates) |
| y at x = 15 % chord | upper +2.449 / lower -2.447 % chord | linear between the published points (UIUC coordinates) |
| y at x = 20 % chord | upper +2.500 / lower -2.498 % chord | linear between the published points (UIUC coordinates) |
| y at x = 25 % chord | upper +2.478 / lower -2.476 % chord | linear between the published points (UIUC coordinates) |
| y at x = 30 % chord | upper +2.411 / lower -2.409 % chord | linear between the published points (UIUC coordinates) |
| y at x = 40 % chord | upper +2.200 / lower -2.199 % chord | linear between the published points (UIUC coordinates) |
| y at x = 50 % chord | upper +1.937 / lower -1.936 % chord | linear between the published points (UIUC coordinates) |
| y at x = 60 % chord | upper +1.640 / lower -1.639 % chord | linear between the published points (UIUC coordinates) |
| y at x = 70 % chord | upper +1.313 / lower -1.312 % chord | linear between the published points (UIUC coordinates) |
| y at x = 80 % chord | upper +0.959 / lower -0.959 % chord | linear between the published points (UIUC coordinates) |
| y at x = 90 % chord | upper +0.582 / lower -0.582 % chord | linear between the published points (UIUC coordinates) |
| y at x = 95 % chord | upper +0.382 / lower -0.382 % chord | linear between the published points (UIUC coordinates) |
| Coordinates source | UIUC Airfoil Coordinates Database: ht08.dat ('HT08') | UIUC Applied Aerodynamics Group (M. Selig) |
Where the files are
Other publishers' files are linked, not hosted. "verify" = check the license at the link before commercial use.
| UIUC Applied Aerodynamics Group (M. Selig) | UIUC Airfoil Coordinates Database: ht08.dat ('HT08') | 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: Mark Drela (HT tail series)) | web | UIUC Airfoil Coordinates Database, public research data; coordinates are facts, cited and linked, not rehosted |
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
| ht08-airfoil-section-100mm-chord | HT08 section, 100 mm chord × 20 mm span, 159 points from the published coordinates, single trailing-edge point (scale to your chord) | STEP · STL |
Let your AI pull this. Add
Set it up →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=ht08-airfoil
Fits with
Free
Clark Y airfoil100.0×20.0×11.71 mm★ 1 fileFree
Eppler E387 airfoil100.0×20.0×9.07 mm★ 1 fileFree
MH 32 airfoil100.0×20.0×8.7 mm★ 1 fileFree
AG35 airfoil (Drela AG series)100.0×20.0×8.72 mm★ 1 fileFree
Selig S7075 airfoil100.0×20.0×9.0 mm★ 1 fileFree
SD7037 airfoil100.0×20.0×9.2 mm★ 1 fileFree
NACA 2412 airfoil100.0×20.0×12.0 mm★ 1 fileFree
NACA 0012 airfoil100.0×20.0×12.0 mm★ 1 file
Questions
How thick is the HT08?
Maximum thickness 5.00 % of chord at 20.2 % chord: 5.00 mm on a 100 mm chord (computed from the UIUC coordinates).
How much camber does the HT08 have?
None: it is symmetric.
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.