Transonic Wind Tunnels
National Aeronautics & Space Administration
U.S. Aerospace Industry
International Installations
National Aeronautics & Space Administation
NASA Ames Research Center
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NASA Langley Research Center
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NASA Marshall Space Flight Center
Wind Tunnel |
Test Section (ft) |
Speed Range (Mach No.) |
Reynolds No. (per ft x 106) |
High Re |
32 in dia |
0.30 - 3.50 |
7 - 200 |
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U. S. Department of Defense
US Air Force Arnold Engineering Development Center
Wind Tunnel |
Test Section (ft) |
Speed Range (Mach No.) |
Reynolds No. (per ft x 106) |
Propulsion Wind Tunnel Facility
16T
4T |
16 x 16
4 x 4 |
0.0 - 1.6
0.1 - 1.3, 1.6, 2.0 |
0.1 - 6.0
2.0 - 6.0 @ M = 1.6 1.3 - 6.1 @ M = 2.0 |
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U. S. Aerospace Industry
The Boeing Company
Wind Tunnel |
Test Section (ft) |
Speed Range (Mach No.) |
Reynolds No. (per ft x 106) |
BTWT |
8 x 12 |
0 - 1.15 |
0 - 4 |
Polysonic |
4 x 4 |
0.20 - 5.8 |
4 - 50 |
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Wind Tunnel |
Test Section (ft) |
Speed Range (Mach No.) |
Reynolds No. (per ft x 106) |
22-in |
22 x 22 in |
0 - 1.15 |
|
66-in |
66 x 66 in |
0 - 1.0 |
0 - 4.5 |
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Lockheed Martin
Wind Tunnel |
Test Section (ft) |
Speed Range (Mach No.) |
Reynolds No. (per ft x 106) |
HSWT |
4 x 4 |
0.4 - 4.8 |
4 - 34 |
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Allied Aerospace Industries - MicroCraft
Wind Tunnel |
Test Section (ft) |
Speed Range (Mach No.) |
Reynolds No. (per ft x 106) |
Tri-Sonic |
7 x 7 ft |
0.1 - 3.5 |
2 - 19 |
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International Wind Tunnels
Australia
Wind Tunnel |
Test Section (m) |
Speed Range (Mach No.) |
Reynolds No.
|
Transonic wind tunnel |
0.806 m x 0.806 m |
0.3 – 1.2, continuously variable. 1.4 with replaceable nozzle |
|
Belgium
Von Karman Institute for Fluid Dynamics
Canada
National Research Council, Institute for Aerospace Research
France
Wind Tunnel |
Test Section (m) |
Speed Range (Mach No.) |
Reynolds No. (x 106) |
S1Ma |
6.74 x 6.27(6.85) 8 m dia |
0.05 - 1.0 |
7.9 |
S2Ma |
1.75 x 1.77 |
0.1 - 1.3 |
5.4 |
S3Ma |
0.56 x 0.78 |
0.1 - 1.3 |
3.5 |
Germany
India
National Aerospace Laboratories
Netherlands
Russia
Central Aerohydrodynamic Institute TsAGI
Wind Tunnel |
Test Section (m) |
Speed Range (Mach No.) |
Reynolds No. (per m x 106) |
T-106 |
2.48 dia |
0.15 - 1.1 |
35 |
T-108 |
1 x 1 |
0.2 - 1.7 |
11 - 20 |
T-109 |
2.25 x 2.25 |
0.4 - 4 |
60 |
TPD |
4 dia |
0.3 - 4 |
60 |
SVS-1 |
0.09, 0.16, 0.22 round |
up to 2.0 |
|
SVS-2 |
0.5 x 0.516, 0.56 round |
0.3 - 6.0 |
110 |
T-112 |
0.6 x 0.6 |
0.6 - 1.8 |
15 |
T-114 |
0.6 x 0.6 |
0.3 - 4 |
20 |
T-115 |
0.15 x 0.20 |
0.2 - 1.2, 2, 3, 4 |
3.8 |
T-128 |
2.75 x 2.75 |
0.15 - 1.7 |
41 |
Institute of Theoretical and Applied Mechanics
Wind Tunnel |
Test Section (m) |
Speed Range (Mach No.) |
Reynolds No. (per m x 106) |
T-325 (BD) |
0.2 x 0.2 |
0.5 - 4 |
20 |
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Sweden
FOI - Swedish Defence Research Agency
Wind Tunnel |
Test Section (m) |
Speed Range (Mach No.) |
Reynolds No. |
T1500 |
4 x 1.5 x 1.5 |
0.20 to 1.25, with slotted walls or 0.20 to 0.80 and 1.3 to 2.0, with solid walls |
Up to 80 million/m |
S4 |
(transonic): 0.92 x 0.90 (supersonic): 0.90 x 1.15 |
0.5 - 2.0 |
800,000 - 1,600,000 /m |
S5 |
(transonic): 0.46 x 0.48 (supersonic): 0.46 x 0.57 |
0.5 - 3.6 |
400,000 - 800,000 /m |
United Kingdom - Great Britain
Flow Science - Goldstein Research Laboratory
DERA
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