List of wind tunnels
From Wikipedia, the free encyclopedia
This is an alphabetical list of wind tunnels.
| Name | Status | Size (W x H x L) | Use | Country | Comments |
|---|---|---|---|---|---|
| A2 Wind Tunnel[1] | 4 m × 94 m × 18 m (14 ft × 310 ft × 58 ft) |
Full scale general purpose | United States | ~$500/hr full scale race car, motorcycle, bicycle | |
| ACE Climatic Wind Tunnel[2] | 6 m × 5.55 m × 14 m (20 ft × 18 ft × 46 ft) |
Full scale: automotive, motorsport, cycling, skiing, architectural, transit, truck, product development | Canada | Available and accessible for all industries requiring wind tunnel services or climatic services | |
| Aerodium Sigulda[3] | Operational | Testing, training, open to the public | Latvia | First vertical wind tunnel in Eastern Europe | |
| AeroDyn Wind Tunnel[4] | Full scale NASCAR racecars | United States | |||
| Aerodynamic and Propulsion Test Unit[5] | Operational | Hypersonic | United States | Located at Arnold Air Force Base and operated by the United States Air Force | |
| Aircraft Research Association[6] | Operational | 2.74 m × 2.44 m × 3.66 m (9 ft 0 in × 8 ft 0 in × 12 ft 0 in) |
Transonic | United Kingdom | Transonic closed circuit, continuous flow wind tunnel. Mach number 0 - 1.4. Reynolds Number 3.5 to 16.7 million/m[7] |
| Auto Research Center[8] | 2.3 m × 2.1 m (7 ft 7 in × 6 ft 11 in) |
Subsonic research and development including: 50% scale model automotive rolling road, wind turbine design and optimization, and cycling | United States | Wind tunnel has a moving ground plane as well as primary and secondary boundary layer suction. Subsonic testing capabilities for motorsports, production cars, commercial semi-trucking, cycling, wind turbines, architecture, aerospace, academic research, and industrial research and development. | |
| RUAG Automotive Wind Tunnel Emmen[9] | Operational | 2.45 m × 1.55 m × 3.8 m (8 ft 0 in × 5 ft 1 in × 12 ft 6 in) |
Low speed automotive and general purpose | Switzerland | Belt system for rolling road simulation |
| Boeing Icing Wind Tunnel[10] | Operational | 1 m × 2 m (4 ft × 6 ft) |
United States | ||
| Boeing Low-speed Aero-Acoustic Facility[11] | Operational | United States | |||
| Boeing Polysonic (supersonic) Wind Tunnel[12] | Operational | 1 m × 1 m (4 ft × 4 ft) |
United States | ||
| Boeing Propulsion Wind Tunnel[13] | Operational | Low-speed, atmospheric, non-return, induction-type facility. Typical models include engine inlets, exhaust nozzles, small engines or powered vehicles, aerodynamic half or full models, as well as thrust reversers. | United States | ||
| Boeing Subsonic (low-speed) Wind Tunnel[14] | Operational | 6 m × 6 m (20 ft × 20 ft) |
United States | ||
| Boeing Transonic Wind Tunnel[15] | Operational | 2 m × 4 m (8 ft × 12 ft) |
United States | ||
| Boundary Layer and Subsonic Wind Tunnel[16] | Operational |
Boundary Layer Test Section: Subsonic Test Section: |
Boundary Layer Development / Low-Speed / Subsonic / General Purpose | United States | |
| Building Research Establishment[17] | Operational | United Kingdom | Two atmospheric boundary layer tunnels | ||
| Cal Poly's Low Speed Wind Tunnel[18] | 1 m × 1 m × 5 m (4 ft × 3 ft × 18 ft) |
Low speed: Scale model testing, Aerospace, Automotive, IR industry | United States | Startups, major Aerospace corporations and other scientific equipment tested here. Rolling road implementation in progress. | |
| Calspan Wind Tunnel[19] | Operational | 2 m × 2 m (8 ft × 8 ft) |
Subsonic / Transonic | United States | The only independently owned and operated wind tunnel in the United States. |
| Central Aerohydrodynamic Institute: T-1 | Diameter 3 m (10 ft) by 6 m (20 ft) |
Russia | |||
| Central Aerohydrodynamic Institute: T-2 | Diameter 6 m (20 ft) by 14 m (46 ft) |
Russia | |||
| Central Aerohydrodynamic Institute: T-5 | Diameter 2.25 m (7 ft 5 in) by 3.15 m (10 ft) |
Russia | |||
| Central Aerohydrodynamic Institute: T-101[20] | 24 m × 14 m × 24 m (79 ft × 46 ft × 79 ft) |
Russia | |||
| Central Aerohydrodynamic Institute: T-102 | 4 m × 2.33 m × 4 m (13 ft × 8 ft × 13 ft) |
Russia | |||
| Central Aerohydrodynamic Institute: T-103 | 4 m × 2.33 m × 3.8 m (13 ft × 8 ft × 12 ft) (elliptical) |
Russia | |||
| Central Aerohydrodynamic Institute: T-104 | Diameter 7 m (23 ft) | Russia | |||
| Central Aerohydrodynamic Institute: T-105[21] | Diameter 4.5 m (15 ft) by 7.5 m (25 ft) |
Vertical wind tunnel | Russia | ||
| Central Aerohydrodynamic Institute: T-106 | Diameter 2.7 m (8 ft 10 in) by 3.5 m (11 ft) |
Russia | |||
| Central Aerohydrodynamic Institute: T-107 | Diameter 2.48 m (8 ft 2 in) by 4.85 m (16 ft) |
Russia | |||
| Central Aerohydrodynamic Institute: T-109 | 2.5 m × 2.5 m × 5.5 m (8 ft 2 in × 8 ft 2 in × 18 ft 1 in) |
Russia | |||
| Central Aerohydrodynamic Institute: T-112 | .6 m × .6 m × 2.55 m (2 ft 0 in × 2 ft 0 in × 8 ft 4 in) |
Russia | |||
| Central Aerohydrodynamic Institute: T-113 | .6 m × .6 m × 1.9 m (2 ft 0 in × 2 ft 0 in × 6 ft 3 in) |
Russia | |||
| Central Aerohydrodynamic Institute: T-113 | .6 m × .6 m × 1.9 m (2 ft 0 in × 2 ft 0 in × 6 ft 3 in) |
Russia | |||
| Central Aerohydrodynamic Institute: T-116 | 1 m × 1 m × 2.35 m (3 ft 3 in × 3 ft 3 in × 7 ft 9 in) |
Russia | |||
| Central Aerohydrodynamic Institute: T-117 | 2.5 m × 2.4 m × 1.9 m (8 ft 2 in × 7 ft 10 in × 6 ft 3 in) |
Russia | |||
| Central Aerohydrodynamic Institute: T-124 | 1 m × 1 m × 4 m (3 ft 3 in × 3 ft 3 in × 13 ft 1 in) |
Russia | |||
| Central Aerohydrodynamic Institute: T-128 | 2.75 m × 2.75 m × 12 m (9 ft 0 in × 9 ft 0 in × 39 ft 4 in) |
Russia | |||
| City, University of London Transonic Wind Tunnel[22] | Operational | 0.91 m (3 ft 0 in) by 0.91 m (3 ft 0 in) by 3 m (9.8 ft); return: 5.7 m (19 ft) by 2.8 m (9 ft 2 in) by 18 m (59 ft) | United Kingdom | Mach 0.4 – 2.0; return max speed 12 m/s. Part of the UK National Wind Tunnel Facility | |
| Cranfield University 8x4 Atmospheric Boundary Layer Wind Tunnel [17] | Operational | 2.4 m (7 ft 10 in) by 1.2 m (3 ft 11 in) | United Kingdom | ||
| Cranfield University 8'x6' Low Speen Wind Tunnel[17][23] | Operational | 2.4 m (7 ft 10 in) by 1.8 m (5 ft 11 in) | United Kingdom | Part of the UK National Wind Tunnel Facility | |
| Cranfield University Weybridge Wind Tunnel[17] | Operational | 1.067 m (3 ft 6.0 in) diameter jet | United Kingdom | ||
| Cranfield University Icing Tunnel[17][24] | Operational | 0.76 m (2 ft 6 in) by 0.76 m (2 ft 6 in); 0.81 m (2 ft 8 in) octagonal; 0.4 m (1 ft 4 in) by 0.4 m (1 ft 4 in) | United Kingdom | Three test sections. Part of the UK National Wind Tunnel Facility | |
| CRIACIV Boundary Layer Wind Tunnel - University of Florence[25] | Operational | 2.44 m × 1.6 m × 10 m (8 ft 0 in × 5 ft 3 in × 32 ft 10 in) |
Building, bridges, general purpose | Italy | Closed circuit wind tunnel, T-shaped diffuser, one atmospheric test section (max speed 31 m/s [100 ft/s]). |
| Durham University 2m tunnel[17][26] | Operational | 2 m2 (22 sq ft) | United Kingdom | Subsonic; turbulence generation system; moving or fixed ground | |
| Durham University 1m recirculating wind tunnel [17][26] | Operational | 0.3 m2 (3.2 sq ft): 0.55 m (1 ft 10 in) by 0.56 m (1 ft 10 in) by 2.44 m (8 ft 0 in) | United Kingdom | 10 mph (4.5 m/s) – 100 mph (45 m/s) | |
| Durham University – smaller tunnels [17] | Operational | 0.2 m2 (2.2 sq ft) | United Kingdom | Three tunnels; max speed 20 m/s | |
| EDITH supersonic wind tunnel[27] | Operational | Diameter 1.2 m (3 ft 11 in) by 1.7 m (5 ft 7 in) |
Long shot time running (20 minutes). | France | Fundamental research on shock waves. Aerodynamic and aerothermal behaviour of probes and models. Fluidic thrust vectoring of supersonic nozzle |
| Energy Technology Centre[17] | Operational | Working section 3.2 m (10 ft) by 3.2 m (10 ft) | Wind blade testing | United Kingdom | |
| European Transonic Wind Tunnel[28] | 2.4 m × 2 m × 9 m (7 ft 10 in × 6 ft 7 in × 29 ft 6 in) |
Transonic | Germany | ||
| Ferrari wind tunnel[29] | Operational | 70 m (230 ft) wide by 80 m (260 ft) long |
Italy | ||
| Focke's wind tunnel[30] | Operational | Germany | Private laboratory of Henrich Focke, not discovered until 1977 | ||
| Glenn L. Martin Wind Tunnel[31] | Operational | 3 m × 236 m (11.04 ft × 775 ft) |
Low speed: scale model testing, automotive, aerospace | United States | University of Maryland, College Park |
| GVPM[32] | Operational | 14 m × 3.8 m × 36 m (46 ft × 12 ft × 118 ft) 4 m × 3.8 m × 4 m |
Building, bridges, rail, aeronautical, general purpose | Italy | Vertically arranged closed circuit wind tunnel with two test sections: one atmospheric (max speed 16 m/s [52 ft/s]), one aeronautical (max speed 55 m/s [180 ft/s]) with possibility to test with open / closed jet. |
| Hypervelocity Wind Tunnel 9[33] | Diameter 1.5 m (5 ft) | United States | Located at Arnold Air Force Base and operated by the United States Air Force | ||
| Imperial College London[17] | Operational | Low speed tunnels: 0.4 m2 (4.3 sq ft) to 4.5 m2 (48 sq ft) | United Kingdom | Five low speed tunnels and other tunnels up to mach 9 | |
| Jules Verne climatic wind tunnel[34][35] | Operational | 6 m × 5 m × 12 m (20 ft × 16 ft × 39 ft) 10 m × 7 m × 20 m 4 m × 2.5 m × 20 m |
Automotive, Rail, Full scale general purpose | France | Three test sections with wind speeds up to 280 km/h (170 mph) |
| Klebanoff–Saric Wind Tunnel[36] | Operational | 1.4 m × 14 m × 4.9 m (4 ft 7 in × 45 ft 11 in × 16 ft 1 in) |
United States | ||
| Large Amplitude Multi-Purpose (LAMP) Vertical Wind Tunnel Bihrle Applied Research[37] | Operational | Diameter 3 m (10 ft) | Vertical, Subsonic, High AOA, Static or body-axis oscillatory | Germany | Privately owned wind tunnel. +- 180 degree AOA and +-90 degree sideslip. Diverse testing capability: static, wind body axis dynamic, Multi-body axis dynamic, simultaneous force moment and pressure data acquisition. |
| RUAG Large Wind Tunnel Emmen[38] | Operational | 7.0 m × 5.0 m × 15.0 m (23 ft × 16 ft × 49 ft) |
Low speed aerospace, full scale automotive and general purpose | Switzerland | |
| Lockheed Martin Low Speed Wind Tunnel[39] | Operational | 8 m × 9 m × 19 m (26 ft × 30 ft × 63 ft) 7.0 m × 4.9 m × 13 m |
Aeronautics, Full Scale Automotive, V/STOL Aircraft, General Purpose | United States | Larger test section was designed for use of V/STOL aircraft but is not limited to such. Max speed of ~320 km/h (200 mph) in smaller test section and ~160 km/h (100 mph) in the larger test section. |
| Loughborough University Aeronautical and Automotive Engineering Low Turbulence Windtunnel[17] | Operational | United Kingdom | AAE Large Windtunnel | ||
| Loughborough University Aeronautical and Automotive Engineering Large Windtunnel[17] | Operational | United Kingdom | |||
| Loughborough University Automotive Wind Tunnel[40] | Operational | 1.92 m (6 ft 4 in) by 1.32 m (4 ft 4 in) by 3.6 m (12 ft) | United Kingdom | 'Rolling road' moving ground plane. Part of the UK National Wind Tunnel Facility | |
| MARHy wind Tunnel[41] | Operational | Diameter 5 m (16 ft) by 2.5 m (8 ft 2 in) |
Hypersonic/supersonic rarefied wind tunnel. No limit running time. Reynolds number /cm: 26.3 < Re < 7522;Mach number: 0.8 < Mach < 20 | France | Fundamental and applied research of fluid dynamic phenomena in rarefied compressible flows. Aerodynamic and aerothermal behaviour of probes and models; Plasma flow control in rarefied and super/hypersonic flows. |
| Modine Wind Tunnels[42] | 2.7 m × 3.3 m × 12.2 m (8 ft 10 in × 10 ft 10 in × 40 ft 0 in) 4.2 m × 4.1 m × 14 m |
United States | Climatic wind tunnel testing, large truck and automotive | ||
| NASA Ames 7-by 10 Foot Wind Tunnel[43] | 2 m × 3 m (7 ft × 10 ft) |
United States | |||
| NASA Ames Hypersonic Propulsion Integration 16 Inch Shock | Diameter 406 mm (16 in) | Hypersonic propulsion | United States | ||
| NASA Ames Hypersonic Propulsion Integration Direct-Connect | Hypersonic propulsion | United States | |||
| NASA Ames National Full Scale Aerodynamic Complex[44] | 12 m × 24 m (40 ft × 80 ft) 24 m × 37 m |
Subsonic | United States | Largest wind tunnel in the world | |
| NASA Ames Subsonic 12 Foot High-Rn Pressure[45] | Diameter 4 m (12 ft) | Subsonic | United States | ||
| NASA Ames 9-by 7-foot Supersonic Wind Tunnel[46] | 3 m × 2 m (9 ft × 7 ft) |
Supersonic | United States | ||
| NASA Ames 11-by 11-foot Transonic Wind Tunnel[47] | 3 m × 3 m (11 ft × 11 ft) |
Transonic | United States | ||
| NASA Ames Unitary Plan Wind Tunnel[48] | Transonic/supersonic | United States | |||
| NASA Glenn 10- by 10-Foot Abe Silverstein Supersonic Wind Tunnel[49] | 3 m × 3 m (10 ft × 10 ft) |
Supersonic, Propulsion and Aero Capability | United States | ||
| NASA Glenn 8- by 6-Foot Wind Tunnel[50] | 2 m × 2 m (8 ft × 6 ft) |
Transonic | United States | ||
| NASA Glenn 9- by 15-Foot Low-Speed Wind Tunnel[51] | 3 m × 5 m (9 ft × 15 ft) |
Subsonic | United States | ||
| NASA Glenn Aero-Acoustic Propulsion Laboratory Nozzle Acoustic Test Rig[52] | Diameter 1,346 mm (53 in) | Acoustic testing of exhaust nozzles, subsonic | United States | Free-jet | |
| NASA Glenn Engine Components Research Lab[53] | United States | ||||
| NASA Glenn Hypersonic Test Facility[54] | Hypersonic | United States | |||
| NASA Glenn Icing Research Tunnel[51] | 3 m × 2 m × 6 m (9 ft × 6 ft × 20 ft) |
Subsonic Icing | United States | ||
| NASA Glenn Propulsion Systems Laboratory[55] | Active | Diameter 7 m (24 ft) by 12 m (38 ft) long |
Full-Scale Engine Testing | United States | Four test cells: 1 & 2 demolished; 3 & 4 active. Cell 3 has icing capabilities |
| NASA Langley 14- by 22-Foot Subsonic Tunnel[51] | 4 m × 7 m (14 ft × 22 ft) |
Subsonic atmospheric | United States | ||
| NASA Langley 20-Foot Vertical Spin Tunnel[51] | Diameter 6 m (20 ft) | Subsonic vertical spin | United States | ||
| NASA Langley Eight-Foot High Speed Tunnel[56]- | Diameter 2 m (8 ft) | High speed | United States | ||
| NASA Langley Full-Scale Wind Tunnel[57] | Demolished | 9 m × 18 m (30 ft × 60 ft) |
Full-scale aircraft | United States | NASA's oldest operating wind tunnel until its closing in October 1995 |
| NASA Langley High-Rn Transonic Dynamics Tunnel[58] | Operational | 5 m × 5 m (16 ft × 16 ft) |
Aeroelasticity, high-risk testing, active controls, rotorcraft performance and stability, transonic aerodynamics. | United States | Unique capability to manipulate fluid-structure scaling parameters with use of Heavy-Gas (R-134a) or air as a test medium and variable pressure.[59] Good flow quality for large transonic tunnel (Mach 0–1.2)[60] |
| NASA Langley Hypersonic 20 Inch Mach 6 Air[61] | Diameter 508 mm (20 in) | Hypersonic | United States | ||
| NASA Langley Hypersonic 20 Inch Mach 6 Tetrafluoromethane[62] | Demolished in 2016[63] | Diameter 508 mm (20 in) | Hypersonic | United States | |
| NASA Langley Hypersonic 31 Inch Mach 10 Air[61] | Diameter 787 mm (31 in) | Hypersonic | United States | ||
| NASA Langley Hypersonic Propulsion Integration 15 Inch Mach 6 High-Temperature Tunnel[64] | Diameter 381 mm (15 in) | Hypersonic | United States | ||
| NASA Langley Hypersonic Propulsion Integration 8 Foot High-Temperature Tunnel[65] | Diameter 2 m (8 ft) | Hypersonic, high-temperature | United States | ||
| NASA Langley Hypersonic Propulsion Integration Arc-Heated Scramjet[66] | Hypersonic | United States | |||
| NASA Langley Hypersonic Propulsion Integration Combustion Scramjet[67] | Hypersonic | United States | |||
| NASA Langley Hypersonic Propulsion Integration Supersonic Combustion[67] | Hypersonic | United States | |||
| NASA Langley NASA / GASL HYPULSE Propulsion Integration[68] | United States | ||||
| NASA Langley National Transonic Facility[69] | 2 m × 2 m (8.2 ft × 8.2 ft) |
Transonic | United States | ||
| NASA Langley Propeller Research Tunnel[70] | Diameter 6 m (20 ft) | Full-scale aircraft used primarily in reducing drag caused by propellers and exposed engines | United States | ||
| NASA Langley Subsonic 12 Foot Atmospheric Lab[71] | Diameter 4 m (12 ft) | Subsonic atmospheric | United States | ||
| NASA Langley Subsonic Low-Turbulence Pressure Tunnel[72] | Subsonic low-turbulence | United States | |||
| NASA Langley Supersonic High-Rn | Supersonic | United States | |||
| NASA Langley Transonic 16 Foot Atmospheric[73] | 5 m (16 ft) |
Transonic atmospheric | United States | ||
| NASA Langley Variable Density Tunnel[70] | Diameter 5 m (15 ft) by 11 m (34.5 ft) long |
Measuring aerodynamic qualities of airfoils | United States | World's first variable density wind tunnel | |
| National Wind Tunnel Facility[74] | Operational | United Kingdom | Twenty-two wind tunnels at twelve universities allowing open access | ||
| ODTÜ-RÜZGEM[75] | Operational |
High Speed Test Section: Boundary Layer Test Section: Open Jet: |
Wind energy, aeronautics, civil engineering | Turkey |
High Speed Test Section: Max speed 100 m/s [330 ft/s], TI<0.25% Boundary Layer Test Section: Max speed 30 m/s [98 ft/s] with spires and roughness elements Open Jet: Max speed 75 m/s (250 ft/s) Interchangeable modular test sections, 6x400 kW axial fan array, 750 kW heat exchanger |
| ONERA Modane S1MA wind tunnel[76] | Operational | Diameter 8 m (26 ft) by 14 m (46 ft) |
Subsonic atmospheric | France | Largest continuous blow-down wind tunnel in the world, Mach 0.05 to 1. |
| ONERA Modane S2MA wind tunnel[77] | Operational | Supersonic | France | Continuous-flow wind tunnel, Variable pressure, Mach 0.1 to Mach 3.0. | |
| PHEDRA (Arc-jet) high enthalpy wind tunnel[78] | Operational | Diameter 4.5 m (15 ft) by 2.1 m (6 ft 11 in) |
Supersonic high enthalpy rarefied wind tunnel. No limit running time . Averaged enthalpy, Mj/kg: few < Ho < 50; Mach number: 2 < Mach < 8;Working gas: N2, Air, CO2, CH4, Ar and extensive mixtures | France | Fundamental research of high enthalpy fluid dynamic phenomena in non-equilibrium flows. Aerodynamic and aerothermal behaviour of probes and models; Atmospheric entry research. |
| Poul la Cour Tunnel[79] | Operational | 3.0 m × 2.0 m (10 ft × 7 ft) |
Airfoil aerodynamics and aeroacoustics, 10 to 105 m/s, Re~7M | Denmark | Named for Poul la Cour |
| Propulsion Wind Tunnel Facility[80] | Operational | Transonic: 4.9 m (16 ft) Supersonic: 4.9 m (16 ft) Aerodynamic trasonic: 1.2 m (4 ft) |
United States | Part of the Arnold Engineering Development Complex located at Arnold Air Force Base and operated by the United States Air Force | |
| Rail Tec Arsenal Climatic Wind Tunnel[81] | Operational | 4.9 m × 5.9 m × 100 m (16 ft × 19 ft × 328 ft) |
Full scale: transit, locomotive, automotive, propeller and turbines, airfoils and aircraft
Icing-, solar-, precipitatoin tests all subsonic |
Austria | RTA operates the longest climatic wind channel in the world. Whole trains up 100 m (330 ft) can be tested under real world conditions from −45 to 60 °C (−49 to 140 °F) and variable climatic conditions. |
| R J Mitchell Wind Tunnel[82] | Operational | 3.5 m × 2.4 m × 10.5 m (11 ft × 8 ft × 34 ft) |
United Kingdom | Largest university owned wind tunnel in the United Kingdom, named for R. J. Mitchell | |
| RWDI Wind Tunnels[83] | Operational | 7.32 m (24 ft) 3.66 m |
Wind engineering, scale buildings | Canada | Two wind tunnels |
| San Diego Wind Tunnel[84] | 4 m × 2 m × 5 m (12 ft × 8 ft × 15 ft) |
United States | Major airframers, bicycle manufacturers and professional athletes | ||
| T3 Hypersonic wind tunnel[85] | Brazil | ||||
| Texas A&M Oran W. Nicks Low Speed Wind Tunnel[86] | 3 m × 2 m × 4 m (10 ft × 7 ft × 12 ft) |
Scale aircraft, UAV, rocket, missile, academic research, automotive, motorsport, cycling, skiing, architectural, transit, truck, product development 0-200MPH | United States | ||
| TitanX Jamestown Vehicle Climatic Wind Tunnel[87] | 3.0 m × 3.5 m (10 ft × 11 ft) |
Climatic testing of vehicle systems and entire trucks | United States | Open for external clients | |
| Trisonic Wind Tunnel[88] | 3,912 mm × 356 mm (154 in × 14 in) |
United States | |||
| Trudelturm[89] | Height 20 m (66 ft) | Germany | |||
| University of Bristol[17] | Operational | Large Low Speed Wind Tunnel 2.1 m (6 ft 11 in) by 1.5 m (4 ft 11 in) Low Turbulence Wind Tunnel 0.8 m (2 ft 7 in) by 0.6 m (2 ft 0 in) Open Jet Wind Tunnel 1.1 m (3 ft 7 in) diameter |
United Kingdom | ||
| University of British Columbia Boundary Layer Wind Tunnel[90] | 2.5 m × 1.6 m × 23.6 m (8 ft 2 in × 5 ft 3 in × 77 ft 5 in) |
Boundary layer, architectural, and wind-engineering studies | Canada | Speed range: 3 to 20 m/s (9.8 to 65.6 ft/s) | |
| University of British Columbia Parkinson Wind Tunnel[91] | 1.0 m × 0.7 m × 2.6 m (3 ft 3 in × 2 ft 4 in × 8 ft 6 in) |
Aeronautical research, studies of flow-induced oscillations, studies of wind tunnel blockage effects | Canada | Speed range: 5 to 35 m/s (16 to 115 ft/s) | |
| University of Glasgow[17] | Operational | De-Havilland Wind Tunnel 2.65 m (8 ft 8 in) by 2.04 m (6 ft 8 in) Handley-Page Wind Tunnel 2.13 m (7 ft 0 in) by 1.61 m (5 ft 3 in) Low Speed Wind Tunnel 1.15 m (3 ft 9 in) by 0.95 m (3 ft 1 in) Flow Visualisation Wind Tunnel 0.90 m (2 ft 11 in) by 0.90 m (2 ft 11 in) |
United Kingdom | ||
| University of Manchester[17] | Operational | Hypersonic wind tunnel 6 in (150 mm) diameter Trisonic wind tunnel 0.15 m (5.9 in) by 0.3 m (1 ft 0 in) Open-circuit boundary layer tunnel 0.9 m (2 ft 11 in) by 0.9 m (2 ft 11 in) by 5 m (16 ft) Open-circuit wind tunnel 1.2 m (3 ft 11 in) by 0.9 m (2 ft 11 in) by 2 m (6 ft 7 in) Open-circuit wind tunnel 0.5 m (1 ft 8 in) by 0.5 m (1 ft 8 in) by 1 m (3 ft 3 in) Closed-circuit water tunnel 0.5 m (1 ft 8 in) by 0.5 m (1 ft 8 in) by 2 m (6 ft 7 in) Tilting flume 0.5 m (1 ft 8 in) by 0.3 m (1 ft 0 in) by 5 m (16 ft) |
United Kingdom | Hypersonic wind tunnel: Mach 4, 5, 6; trisonic wind tunnel: Mach 0 to 0.8, 1.8 | |
| University of Southampton[17] | Operational | 3' x 2' tunnel 0.9 m (2 ft 11 in) by 0.6 m (2 ft 0 in) by 4.5 m (15 ft) 7' x 5' tunnel 2.1 m (6 ft 11 in) by 1.5 m (4 ft 11 in) R J Mitchell Wind Tunnel 3.5 m (11 ft) by 2.4 m (7 ft 10 in) |
United Kingdom | ||
| University of Surrey[17] | Operational | EnFlo Laboratory meteorological wind tunnel 3.5 m (11 ft) by 1.5 m (4 ft 11 in) by 20 m (66 ft) | United Kingdom | ||
| University of Washington Aeronautical Laboratory, Kirsten Wind Tunnel[92] | 2 m × 4 m × 3 m (8 ft × 12 ft × 10 ft) |
Subsonic | United States | ||
| University of Washington Department of Aeronautics & Astronautics 3x3[93] | 1 m × 1 m × 2 m (3 ft × 3 ft × 8 ft) |
Velocity range approx. 32 to 217 km/h (20 to 135 mph) | United States | The original "Boeing Aerodynamical Chamber", built in 1918 with an Eiffel 1.2 by 1.2 m (4 by 4 ft) and updated in the early 1990s with new power systems and a higher velocity EDL 0.91 by 0.91 m (3 by 3 ft) | |
| Virginia Tech Stability Wind Tunnel[94] | 2 m × 2 m (6 ft × 6 ft) |
United States | |||
| Von Karman Gas Dynamics Facility[95] | Operational | United States | Three tunnels at the Arnold Engineering Development Complex | ||
| Williams F1 Wind Tunnel 2[96] | Operational | 4.4 m × 2.5 m × 12 m (14 ft × 8 ft × 39 ft) |
Motorsport / Automotive | United Kingdom | |
| WindShear Full Scale, Rolling Road, Automotive Wind Tunnel[97] | Wind shear | United States | |||
| Windtech Boundary Layer Wind Tunnel[98] | Operational | 3 m × 2 m × 23 m (10 ft × 7 ft × 75 ft) |
Low-Speed / Boundary Layer Wind Tunnel | Australia | Windtech owns and operates one of the largest boundary layer wind tunnel labs in the world with a total of 3 wind tunnels under one roof. Each wind tunnel is 3 m × 2 m × 23 m (9.8 ft × 6.6 ft × 75.5 ft) |