Transonic Wind Tunnels
National Aeronautics & Space Administration
 | NASA Ames Research Center |
| NASA Langley Research Center |
| NASA Marshall Space Flight Center |
United States Department of Defense
| US Air Force Arnold Engineering Development Center |
U.S. Aerospace Industry
| Boeing |
| Aero Systems Engineering |
| Lockheed Martin |
| Allied Aerospace Industries - MicroCraft |
| Verdian - Calspan Operation |
International Installations
| India
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| Japan | ||
| Netherlands
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| Russia
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| Sweden
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| United Kingdom
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National Aeronautics & Space Administation
NASA Ames Research Center
| Wind Tunnel | Test Section (ft) | Speed Range (Mach No.) |
Reynolds No. (per ft x 106) |
| 11 - ft (Unitary) | 11 x 11 x 22 | 0.20 - 1.50 | 0.3 - 9.6 |
NASA Langley Research Center
| Wind Tunnel | Test Section (ft) | Speed Range (Mach No.) |
Reynolds No. (per ft x 106) |
| 16-ft Transonic Tunnel | 15.5 x 15.5 | 0.2 - 1.25 | 1. to 4. |
| 0.3M Transonic Cryogenic Tunnel | 8 x 24 in | 0.2 - 0.9 | 1 to 100 |
| National Transonic Facility | 8.2 x 8.2 | 0.1 - 1.2 | 4 to 146 |
| Transonic Dynamics Tunnel (TDT) | 16 x 16 | 0.1 - 1.2 | 0.03 to 3 (Air) 0.2 to 10 (R-134a) |
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 |
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 |
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 |
Aero Systems Engineering
| 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 |
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 |
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 |
Veridian - Calspan Operations
| Wind Tunnel | Test Section (ft) | Speed Range (Mach No.) |
Reynolds No. (per ft x 106) |
| Calspan | 8 x 8 ft | 0 - 1.35 | 0 - 12.5 |
International Wind Tunnels
Australia
Defense Science and Technology Organization
| 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 |
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Belgium
Von Karman Institute for Fluid Dynamics
| Wind Tunnel | Test Section (m) | Speed Range (Mach No.) |
Reynolds No. |
| Transonic/supersonic wind tunnel S-1 | 40 cm x 40 cm | 0.4 to 1.05, 1.43 2.0 and 2.25 |
4 x 106 /m |
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Canada
National Research Council,
Institute for Aerospace Research
| Wind Tunnel | Test Section (m) | Speed Range (Mach No.) |
Reynolds No. |
| Pilot Blowdown Wind Tunnel | 1/12 scale of 1.5m Blowdown | ||
| 1.5m Transonic Blowdown Wind Tunnel | 1.5m x 1.5m | 0.1 to 0.75 subsonic 0.7 to 1.4 transonic 1.1 to 4.25 supersonic |
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France
Onera
| 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 |
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Germany
DLR - German Aerospace Center
| Wind Tunnel | Test Section (m) | Speed Range (Mach No.) |
Reynolds No. (x107)/m |
| VMK Vertical Test Section |
Nozzel exit dia 150, 230, and 310 mm |
0.4 - 0.9, 1.57 - 3.2 | 25 |
| TMK Trisonic Wind Tunnel |
60 x 60 cm | 0.5 - 5.7 | 0.7 to 7 |
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DNW - German-Dutch Wind Tunnels
| Wind Tunnel | Test Section (m) | Speed Range (Mach No.) |
Reynolds No. (x106) |
| TWG Transonic Wind Tunnel |
1 x 1 | 0.3 < M
< 0.9 (Subsonic Test Section) (0.5) - 0.85 < M < 1.2, (Transonic Test Section) 1.33 < M < 2.21 (Supersonic Test Section) |
1.8 |
| KRG - Cryogenic Ludwieg-Tube | cross section of 0.4 x 0.35² and a length of 2 m | 0.30 < M < 0.95 | 78 |
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India
National Aerospace Laboratories
| Wind Tunnel | Test Section (m) | Speed Range (Mach No.) |
Reynolds No. (x 106) |
| 1.2m Trisonic Tunnel (H1) | 1.2 x 1.2 | 0.20 - 4.0 | |
| 0.6m Transonic Tunnel (H2) | 0.6 x 0.6 | 0.20 - 1.2 |
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Netherlands
DNW - German-Dutch Wind Tunnels
| Wind Tunnel | Test Section (m) | Speed Range (Mach No.) |
Reynolds No. (x 106) |
| CSST - Continuous Supersonic Tunnel |
0.27 x 0.27 | M = 0.3 - 4 | 4 |
| HST | rectangular cross section 2.00 x 1.60 or 1.80 |
M = 0 to 1.35 | 9 |
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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 |
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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 |
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 |
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United Kingdom - Great Britain
Flow Science - Goldstein Research Laboratory
| Wind Tunnel | Test Section (m) | Speed Range (Mach No.) |
Reynolds No. |
| 0.21m x 0.15m Transonic / Supersonic Wind Tunnel | 0.21 m x 0.15 m rectangular cross section with slotted walls by 0.6 m long | Mach 0.3 to Mach 0.9 |
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Aircraft Research
Association
| Wind Tunnel | Test Section (m) | Speed Range (Mach No.) |
Reynolds No. (per m) |
| Transonic Wind Tunnel (TWT) | 2.74 x 2.44 | 0.2 - 1.4 | |
| Two Dimensional Tunnel (2DT) | 203 mm x 475 mm | 0.3 - 0.87 | |
| Small Transonic Wind Tunnel (Z4T) | 0.23 x 0.20 | 0.3 - 1.3 | 15 x 106 |
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DERA
| Wind Tunnel | Test Section (m) | Speed Range (Mach No.) |
Reynolds No. (per meter) |
| 8 x 8 Pressurized High Speed | 8ft x 8ft |