Hypersonic Wind Tunnels
National Aeronautics & Space Administration
 | NASA Langley Research Center |
| NASA Glenn Research Center |
United States Department of Defense
| Arnold Engineering Development Center |
U.S. Aerospace Industry
| Boeing |
| Aero Systems Engineering |
| Verdian - Calspan Operation |
| Calspan - University of Buffalo Research Center (CUBRC) |
International Installations
| Belgium
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| France
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| Germany
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| Russia
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| Sweden
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| United Kingdom
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National Aeronautics & Space Administration
NASA Langley Research Center
| Wind Tunnel | Test Section (ft) | Speed Range (Mach No.) |
Reynolds No. (per ft x 106) |
| 15-in Mach 6 High Temperature Tunnel | 15 in dia | 6 | 0.5 to 8.0 |
| 20-in Mach 6 tunnel | 20 in dia | 6 | 0.5 - 9 |
| 20-in Mach 6 CF4 Tunnel | 20 in dia | 6 | 0.5 to 0.7 |
| 31-in Mach 10 Tunnel | 31 in dia | 10 | 0.2 - 2.2 |
| Direct Connect Supersonic Combustion Test Facility | (Mach 2.0 nozzle) 1.52 in x 3.46 in (Mach 2.7 nozzle) |
4.0 to 7.5 | 1.8 to 31.0 |
| Combustion-Heated Scramjet Test Facility | 42 in x 30 in x 96 in | 3.5 to 6.0 | 1 to 6.8 |
| Arc-Heated Scramjet Test Facility | 4 ft dia | 4.7 to 8.0 | 0.04 to 2.2 |
| 8-ft high Temperature Tunnel | 8-ft dia | 4, 5, 7 | 0.3 - 5.09 |
NASA Glenn Research Center
| Wind Tunnel | Test Section (ft) | Speed Range (Mach No.) |
Reynolds No. (per ft x 106) |
| Hypersonic Tunnel Facility | 42 in dia x 120 in | 5 - 7 | 0.97 at Mach 7 to 2.41 at Mach 5 |
U.S. Department of Defense
Arnold Engineering Development Center
| Wind Tunnel Facility | Test Section (ft) |
Speed Range (Mach No.) |
Reynolds No. (per ft x 106) |
| Aerodynamic and Propulsion Test Unit | |||
| Von Karman Gas Dynamics Facility | |||
| High Pressure ARCS | |||
| Hypervelocity Tunnel No. 9 | 5 dia | 7, 8, 10, 14, 16.5 | 0.072 at Mach 14 to 55.7 at Mach 8 |
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U. S. Aerospace Industry
Aero Systems Engineering
| Wind Tunnel | Test Section (ft) | Speed Range (Mach No.) |
Reynolds No. (per ft x 106) |
| High Area Ratio Nozzle Test Stand and Hypersonic Wind Tunnel | 20 in dia | 7, 11, 14 |
Boeing
| Wind Tunnel | Test Section (ft) | Speed Range (Mach No.) |
Reynolds No. (per ft x 106) |
| B30 HST | 12-inch diameter contoured nozzle 30-inch contoured nozzle |
Mach = 5 - 8 Mach = 8 - 20 |
Veridian - Calspan Operations
| Wind Tunnel | Test Section (ft) | Speed Range (Mach No.) |
Reynolds No. (per ft) |
| Calspan 48 in shock tube | 48 in dia | 5 - 18 | 104-4x107 |
| Calspan 96 in shock tube | 96 in dia | 7 - 19 | 104-7x107 |
CUBRC
| Wind Tunnel | Test Section (ft) | Speed Range (Mach No.) |
Reynolds No. (per ft) |
| LENS | 8 ft dia | 5.5 - 15 | |
| LENS II | 8 ft dia | 3 - 8 |
International Installations
Belgium
Von Karman Institute for Fluid Dynamics
| Wind Tunnel | Test Section (m) | Speed Range (Mach No.) |
Reynolds No. |
| Hypersonic wind tunnel H-3 | 12 cm diameter | Mach 6 | 3 x 106 to 30 x 106 /m |
| Longshot free piston hypersonic wind tunnel | a Mach 14 contoured nozzle of 0.43 m exit diameter and a 6 degree conical nozzle of 0.60 m exit diameter | 15 to 20 | 5 x 106 to 15 x 106 /m |
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France
Onera
| Wind Tunnel | Test Section (m) | Speed Range (Mach No.) |
Reynolds No. (x 106) |
| S4Ma | dia = 0.68, or 1, or 1 | 6.4, 10, 12 | 1.7, 0.9, 0.35 |
| F4 | dia = 670mm, or 670mm, or 430mm, or 930mm | 8-17, 7-13, 6-11, 9-21 | 2, 3, 5 ,1 |
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Germany
DLR - German Aerospace Center
| Wind Tunnel | Test Section (m) | Speed Range (Mach No.) |
Reynolds No. (x106)/m |
| L2K Arc-heated Facility |
Nozzle exit dia 100, & 200 mm |
4 to 8 | up to 0.01 |
| L3K Arc-heated Facility |
Nozzle exit dia 100, 200, 300, & 400 mm |
5 to 10 | up to 0.1 |
| H2K Hypersonic Wind Tunnel |
36 cm 60 cm |
4.8 5.3, 6.0, 7.0, 8.7, and 11.2. |
20 |
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DNW - German-Dutch Wind Tunnels
| Wind Tunnel | Test Section (m) | Speed Range (Mach No.) |
Reynolds No. (x106) |
| RWG Ludwieg-Tube Wind Tunnel |
two sections: 0.5 x 0.5 & 0.5 dia |
Leg A: 3, & 4 Leg B: 5, 6, & 6.8 |
3.25 (Leg A) 2.2 (Leg B) |
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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-116 | 1 x 1 | 1.8 - 10 | 47 |
| T-117 | 2.5 x 2.4 x 1.9 | 10 - 18 | 4 |
| T-120 | 0.15 dia | 4 - 10 | 67 |
| T-121 | 0.2 x 0.2 m ( M up to 6.0 ) 0.2 m ( M from 6.0 to 9.0 ) |
4 - 9 | 50 |
| IT-2 | Diameter: 0.44 m (contoured nozzle) 0.2, 0.53, 0.9 m (conical nozzle) |
16.3 - 17.9 w/contoured nozzels, 10 - 22 w/conical nozzels |
40 |
| ST-1 | 5 - 10 | 5.3 | |
| VAT-3 | 1 | 12, 18 Contoured nozzles 20 Conical nozzles |
0.03 - 1.5 |
| T-131 | 1.2 | 5 - 7 2, 2.5, 3, 3.5, 4 w/ supersonic test rig |
10 |
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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-326 (BD) | 0.2 dia | 5 - 14 | 4 |
| T-327 (VC) | 0.22 dia | 16 - 25 | 0.2 |
| UT-302 (HS) | 0.3 dia | 5 - 15 | 100 |
Sweden
FOI - Swedish Defence Research Agency
| Wind Tunnel | Test Section (m) | Speed Range (Mach No.) |
Reynolds No. (per meter) |
| HYP500 | (open Jet) 500 mm nozzle diameter | 4, 7 |
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United Kingdom - Great Britain
Flow Science - Goldstein Research Laboratory
| Wind Tunnel | Test Section (m) | Speed Range (Mach No.) |
Reynolds No. |
| Mark II Tube | 200 mm x 50 mm | mach numbers to 15 | |
| Mark III Tube | 60 mm square section | mach numbers to 15 |
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Imperial College
| Wind Tunnel | Test Section (m) | Speed Range (Mach No.) |
Reynolds No. |
| Hypersonic Gun Tunnel | 0.34 m dia | 9 | 40 x 106 |
| Low Density Hypersonic Wind Tunnel | 0.20 m dia | 25 |
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Aircraft Research
Association 
| Wind Tunnel | Test Section (m) | Speed Range (Mach No.) |
Reynolds No. (per m) |
| Hypersonic Wind Tunnels (HWT) | 0.3 x 0.4 | 4 - 5 | 60 x 106 (at Mach 4) 40 x 106 (at Mach 5) |
| Hypersonic Wind Tunnels (HWT) | 0.3 dia | 6, 7, 8 | 70 x 106 (at Mach 6) 50 x 106 (at Mach 7) 30 x 106 (at Mach 8) |