NameStatusSize (W x H x L)UseLocationComments
Windtech Boundary Layer Wind Tunnel Operational 3.0 m × 2.0 m × 23.0 m (9.8 ft × 6.6 ft × 75 ft) Low-Speed / Boundary Layer Wind Tunnel Bexley, Australia WINDECH 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 3.0m wide, 2.0m high and has a fetch length of 23m.
A2 wind tunnel 4.3 m × 3.0 m × 6.1 m (14 ft × 9.8 ft × 20 ft) Full scale general purpose Mooresville, NC, USA ~$500/hr full scale race car, motorcycle, bicycle
ACE Climatic Wind Tunnel 6 m × 5.55 m × 14 m (20 ft × 18 ft × 46 ft) Full scale: automotive, motorsport, cycling, skiing, architectural, transit, truck, product development Oshawa, Ontario, Canada Available and accessible for all industries requiring wind tunnel services or climatic services
Lockheed Martin Low Speed Wind Tunnel (LSWT) Operational 7.9 m × 9.0 m (26 ft × 30 ft)

7.0 m × 4.9 m (23 ft × 16 ft)

 Aeronautics, Full Scale Automotive, V/STOL Aircraft, General Purpose Marietta, GA, USA Larger test section was designed for use of V/STOL aircraft but is not limited to such. Max speed of ~200 mph in smaller test section and ~100 mph in the larger test section.
ACE Climatic Wind Tunnel 6 m × 5.55 m × 14 m (20 ft × 18 ft × 46 ft) Full scale: automotive, motorsport, cycling, skiing, architectural, transit, truck, product development Oshawa, Ontario, Canada Available and accessible for all industries requiring wind tunnel services or climatic services
AeroDyn Wind Tunnel Full scale NASCAR racecars Mooresville, NC, USA
Aircraft Research Association Ltd (ARA) Operational 2.7 m × 2.4 m (8 ft 10 in × 7 ft 10 in) Bedford, UK Transonic closed circuit, continuous flow wind tunnel. Mach number 0 - 1.4. Reynolds Number 3.5 to 16.7 million/m[1]
Automotive Wind Tunnel Emmen (LWTE) 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 Emmen, Switzerland Belt system for rolling road simulation
Auto Research Center (ARC) 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 Indianapolis, IN, USA 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.
Boeing Icing Wind Tunnel – BRAIT Operational 1.22 m × 1.83 m (4 ft 0 in × 6 ft 0 in) Seattle, WA
Boeing Low-speed Aero-Acoustic Facility – LSAF Operational Seattle, WA
Boeing Polysonic (supersonic) Wind Tunnel – PSWT Operational 1.22 m × 1.22 m (4 ft 0 in × 4 ft 0 in) St. Louis, MO
Boeing Propulsion Wind Tunnel - BPWT (9x9) Operational 2.74 m × 2.74 m (9 ft 0 in × 9 ft 0 in) 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. Seattle, WA
Boeing Subsonic (low-speed) Wind Tunnel - BVWT Operational 6.1 m × 6.1 m (20 ft × 20 ft) Philadelphia, PA Contact Boeing Technology Services for additional information about or to use Boeing Facilities[2]
Boeing Transonic Wind Tunnel – BTWT Operational 2.44 m × 3.67 m (8 ft 0 in × 12 ft 0 in) Seattle, WA
Cal Poly's Low- Speed Wind Tunnel 1.22 m × .9144 m × 4.27 m (4 ft 0 in × 3 ft 0 in × 14 ft 0 in) Low speed: Scale model testing, Aerospace, Automotive, IR industry San Luis Obispo, CA, USA Startups, major Aerospace corporations and other scientific equipment tested here. Rolling road implementation in progress.
Calspan Wind Tunnel Operational 2.44 m × 2.44 m (8 ft 0 in × 8 ft 0 in) Subsonic / Transonic Buffalo, New York, USA The only independently owned and operated wind tunnel in the United States.
Central Aerohydrodynamic Institute: T-1 3 m (9.8 ft) diameter x 6 m (20 ft) Zhukovsky, Russia
Central Aerohydrodynamic Institute: T-2 6 m (20 ft) diameter x 14 m (46 ft) Zhukovsky, Russia
Central Aerohydrodynamic Institute: T-5 2.25 m (7 ft 5 in) diameter x 3.15 m (10 ft) Zhukovsky, Russia
Central Aerohydrodynamic Institute: T-101 24 m × 14 m × 24 m (79 ft × 46 ft × 79 ft)[3] Zhukovsky, Russia
Central Aerohydrodynamic Institute: T-102 4 m × 2.33 m × 4 m (13 ft × 7.6 ft × 13 ft) Zhukovsky, Russia
Central Aerohydrodynamic Institute: T-103 4 m × 2.33 m × 3.8 m (13 ft × 7.6 ft × 12 ft) (elliptical) Zhukovsky, Russia
Central Aerohydrodynamic Institute: T-104 7 m (23 ft) diameter Zhukovsky, Russia
Central Aerohydrodynamic Institute: T-105 4.5 m (15 ft) diameter x 7.5 m (25 ft)[4] Vertical Zhukovsky, Russia
Central Aerohydrodynamic Institute: T-106 2.7 m (8 ft 10 in) diameter x 3.5 m (11 ft) Zhukovsky, Russia
Central Aerohydrodynamic Institute: T-107 2.48 m (8 ft 2 in) diameter x 4.85 m (16 ft) Zhukovsky, 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) Zhukovsky, 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) Zhukovsky, 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) Zhukovsky, 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) Zhukovsky, 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) Zhukovsky, 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) Zhukovsky, Russia
Central Aerohydrodynamic Institute: T-124 1 m × 1 m × 4 m (3 ft 3 in × 3 ft 3 in × 13 ft 1 in) Zhukovsky, 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) Zhukovsky, Russia
CRIACIV Boundary Layer Wind Tunnel - University of Florence 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 Prato - Italy Closed circuit wind tunnel, T-shaped diffuser, one atmospheric test section (max speed 31 m/s).
CSTB Jules Verne Wind Tunnel operational
  • 6 m × 5 m × 12 m (20 ft × 16 ft × 39 ft)[5]
  • 10 m × 7 m × 20 m (33 ft × 23 ft × 66 ft)[6]
  • 4 m × 2.5 m × 20 m (13 ft × 8.2 ft × 66 ft)[7]
 Automotive, Rail, Full scale general purpose CSTB Nantes, France Three test sections with wind speeds up to 280 km/h
EDITH supersonic wind tunnel (Experimental plateform FAST) operational 1.2 m (3 ft 11 in) diameter x 1.7 m (5 ft 7 in) Long shot time running (20 minutes). Laboratoire ICARE, CNRS, Orleans, FRANCE Fundamental research on shock waves. Aerodynamic and aerothermal behavior of probes and models. Fluidic thrust vectoring of supersonic nozzle
European transonic wind tunnel 2 m × 2.4 m × 9 m (6 ft 7 in × 7 ft 10 in × 29 ft 6 in) Transonic Cologne, Germany
Glenn L. Martin Wind Tunnel 2.36 m × 3.35 m (7 ft 9 in × 11 ft 0 in) Low speed: scale model testing, automotive, aerospace University of Maryland, College Park, Maryland, USA
GVPM Operational
  • 14 m × 3.8 m × 36 m (46 ft × 12 ft × 120 ft);
  • 4 m × 3.8 m × 4 m (13 ft × 12 ft × 13 ft)
 Building, bridges, rail, aeronautical, general purpose Milano - Italy Vertically arranged closed circuit wind tunnel with two test sections: one atmospheric (max speed 16 m/s), one aeronautical (max speed 55 m/s) with possibility to test with open / closed jet.
Large Amplitude Multi-Purpose (LAMP) Vertical Wind Tunnel Bihrle Applied Research Operational 3.05 m (10 ft) diameter Vertical, Subsonic, High AOA, Static or body-axis oscillatory Neuburg a.d. Donau, 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.
Large Wind Tunnel Emmen (LWTE) 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 Emmen, Switzerland
MARHy wind tunnel(Experimental plateform FAST) operational 5 m (16 ft) diameter x 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 Laboratoire ICARE, CNRS, Orleans, FRANCE Fundamental and applied research of fluid dynamic phenomena in rarefied compressible flows. Aerodynamic and aerothermal behavior of probes and models;Plasma flow control in rarefied and super/hypersonic flows.
Modine Wind Tunnels
  • 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 (14 ft × 13 ft × 46 ft)
 Racine, Wisconsin, USA Climatic wind tunnel testing, large truck and automotive
NASA Ames 7×10 foot Wind Tunnel (operated by the US Army) 2.13 m × 3.05 m (7 ft 0 in × 10 ft 0 in) Mountain View, California, USA
NASA Ames Hypersonic Propulsion Integration 16 Inch Shock .41 m (1 ft 4 in) diameter Hypersonic propulsion Mountain View, CA, USA
NASA Ames Hypersonic Propulsion Integration Direct-Connect Hypersonic propulsion Mountain View, CA, USA
NASA Ames National Full Scale Aerodynamic Complex (operated by the US Air Force)
  • 24.38 m × 37 m (80 ft × 120 ft);
  • 12 m × 24 m (39 ft × 79 ft)
 Subsonic Mountain View, California, USA Largest wind tunnel in the world
NASA Ames Subsonic 12 Foot High-Rn Pressure 3.66 m (12 ft) diameter Subsonic Mountain View, CA, USA
NASA Ames Supersonic 9×7 Foot High-Rn 2.74 m × 2.13 m (9 ft 0 in × 7 ft 0 in) Supersonic Mountain View, CA, USA
NASA Ames Transonic 11 Foot High-Rn 3.35 m (11 ft) diameter Transonic Mountain View, CA, USA
NASA Ames Unitary Plan Wind Tunnel Mountain View, CA, USA
NASA Glenn Hypersonic Test Facility Hypersonic Sandusky, Ohio, USA
NASA Glenn 10- by 10-Foot Abe Silverstein Supersonic Wind Tunnel 3.05 m × 3.05 m (10 ft × 10 ft) Supersonic Cleveland, OH, USA
NASA Glenn 9- by 15-Foot Wind Tunnel 2.74 m × 4.57 m (9 ft 0 in × 15 ft 0 in) Subsonic Cleveland, OH, USA
NASA Glenn 8- by 6-Foot Wind Tunnel 2.44 m × 1.83 m (8 ft 0 in × 6 ft 0 in) Transonic Cleveland, OH, USA
NASA Glenn Aero-Acoustic Propulsion Laboratory Nozzle Aeroacoustic Test Rig 1.300 m (4 ft 3 in) diameter Acoustic testing of exhaust nozzles, subsonic Cleveland, OH, USA Free-jet
NASA Glenn Engine Components Research Lab Cleveland, OH, USA
NASA Glenn Icing Research Tunnel Subsonic Icing Cleveland, OH, USA
NASA Glenn Propulsion Systems Laboratory active Full-Scale Engine Testing Cleveland, OH, USA Four test cells: 1 & 2 demolished; 3 & 4 active. Cell 3 has icing capabilities
NASA Langley 30-by-60-Foot Full-Scale Wind Tunnel

[8]

 demolished 9.144 m × 18.288 m (30 ft × 60 ft) Full-scale aircraft Hampton, Virginia, USA NASA's oldest operating wind tunnel until its closing in October 1995
NASA Langley Eight-Foot High Speed Tunnel

[9]

 2.44 m (8 ft 0 in) diameter High speed Hampton, Virginia, USA
NASA Langley Hypersonic 20 Inch Mach 6 Air .508 m (1 ft 8 in) diameter Hypersonic Hampton, VA
NASA Langley Hypersonic 31 Inch Mach 10 Air .78 m (2 ft 7 in) diameter Hypersonic Hampton, VA, USA
NASA Langley Hypersonic 20 Inch Mach 6 Tetrafluoromethane Demolished in 2016[10] .508 m (1 ft 8.0 in) diameter Hypersonic Hampton, VA, USA
NASA Langley Hypersonic Propulsion Integration 8 Foot High-Temperature Tunnel 2.44 m (8 ft 0 in) diameter Hypersonic, high-temperature Hampton, VA, USA
NASA Langley Hypersonic Propulsion Integration Arc-Heated Scramjet Hypersonic Hampton, VA, USA
NASA Langley Hypersonic Propulsion Integration Combustion Scramjet Hypersonic Hampton, VA, USA
NASA Langley Hypersonic Propulsion Integration Supersonic Combustion Hypersonic Hampton, VA
NASA Langley Hypersonic Propulsion Integration 15 Inch Mach 6 High-Temperature Tunnel .381 m (1 ft 3 in) diameter Hypersonic Hampton, VA, USA
NASA Langley Subsonic 12 Foot Atmospheric Lab 3.66 m (12 ft) diameter Subsonic atmospheric Hampton, VA, USA
NASA Langley Subsonic 20 Foot Vertical Spin Tunnel 6.10 m (20 ft) diameter Subsonic vertical spin Hampton, VA, USA
NASA Langley Subsonic 14×22 foot Atmospheric 4.27 m × 6.71 m (14 ft × 22 ft) Subsonic atmospheric Hampton, VA, USA
NASA Langley Subsonic Low-Turbulence Pressure Tunnel Subsonic low-turbulence Hampton, VA, USA
NASA Langley Supersonic High-Rn Supersonic Hampton, VA, USA
NASA Langley High-Rn Transonic Dynamics Tunnel Operational 4.88 m × 4.88 m (16 ft × 16 ft) Aeroelasticity, high-risk testing, active controls, rotorcraft performance and stability, transonic aerodynamics. Hampton, VA, USA Unique capability to manipulate fluid-structure scaling parameters with use of Heavy-Gas (R-134a) or air as a test medium and variable pressure.[11] Good flow quality for large transonic tunnel (Mach 0–1.2)[12]
NASA Langley Transonic 16 Foot Atmospheric 4.88 m (16 ft) Transonic atmospheric Hampton, VA, USA
NASA Langley National Transonic Facility Transonic Hampton, VA, USA
NASA Langley NASA/GASL HYPULSE Propulsion Integration Hampton, VA, USA
ONERA Modane wind tunnel Operational 8 m (26 ft) diameter x 14 m (46 ft)[13] Subsonic atmospheric ONERA Modane, France Largest continuous blow-down wind tunnel in the world, Mach 0.05 to 1.[14]
PHEDRA (Experimental plateform FAST) operational 4.5 m (15 ft) diameter x 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 Laboratoire ICARE, CNRS, Orleans, FRANCE Fundamental research of high enthalpy fluid dynamic phenomena in non-equilibrium flows. Aerodynamic and aerothermal behavior of probes and models; Atmospheric entry research.
Poul la Cour Tunnel (PLCT) operational 3.0 m × 2.0 m (9.8 ft × 6.6 ft) Airfoil aerodynamics and aeroacoustics, 10 to 105 m/s, Re~7M DTU Wind Energy, Roskilde, Denmark
RWDI Wind Tunnels operational
  • 7.32 m (24 ft);
  • 3.66 m (12 ft)[15]
 Wind engineering, scale buildings Guelph, Ontario, Canada Two wind tunnels
San Diego Wind Tunnel San Diego, CA, USA Major airframers, bicycle manufacturers and professional athletes
Texas A&M Oran W. Nicks Low Speed Wind Tunnel 3.66 m × 3.05 m × 2.13 m (12 ft × 10 ft × 7.0 ft) Scale aircraft, UAV, rocket, missile, academic research, automotive, motorsport, cycling, skiing, architectural, transit, truck, product development 0-200MPH Texas A&M University, College Station, TX, USA
TitanX Jamestown Vehicle Climatic Wind Tunnel 3.0 m × 3.5 m (9.8 ft × 11 ft) Climatic testing of vehicle systems and entire trucks Jamestown, NY, USA Open for external clients
Trisonic wind tunnel El Segundo, California, USA
University of British Columbia Boundary Layer Wind Tunnel 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 Vancouver, BC, Canada Speed Range: 3 m/s to 20 m/s
University of British Columbia Parkinson Wind Tunnel 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 Vancouver, BC, Canada Speed Range: 5 m/s to 35 m/s
University of Washington Aeronautical Laboratory ("UWAL"), Kirsten Wind Tunnel 2.44 m × 3.66 m (8 ft 0 in × 12 ft 0 in) Subsonic Seattle, WA, USA
University of Washington Dept. of Aero&Astro 3X3 1.097 m × 1.097 m (3 ft 7 in × 3 ft 7 in) Velocity range approx. 20 to 135 mph Seattle, WA, USA The original "Boeing Aerodynamical Chamber", built in 1918 with an Eiffel 4 ft by 4 ft and updated in the early 1990s with new power systems and a higher velocity EDL 3 ft by 3 ft
Variable Density Tunnel Variable density Hampton, Virginia, USA
Virginia Tech Stability Wind Tunnel 1.83 m × 1.83 m (6 ft 0 in × 6 ft 0 in) Blacksburg, Virginia
Williams F1 Wind Tunnel 2 Operational 4.4 m x 2.5 m x 12 m Motorsport / Automotive Oxfordshire, UK
Wind Shear's Full Scale, Rolling Road, Automotive Wind Tunnel Wind shear Concord, NC, USA
Boundary Layer and Subsonic Wind Tunnel (BLAST) at University of Texas at Dallas Operational Boundary Layer Test Section:2.8 m (W) x 2.1 m (H) x 30 m (L)

Subsonic Test Section: 2.1 m (W) x 2.1 m (H) x 4 m (L)[16]

 Boundary Layer Development / Low-Speed / Subsonic / General Purpose Richardson, TX, USA
ODTÜ-RÜZGEM Large Scale Wind Tunnel at The Middle East Technical University (METU) Operational High Speed Test Section: 2.5 m (W) x 2.5 m (H) x 10 m (L)

Boundary Layer Test Section: 7 m (W) x 3 m (H) x 20 m (L)

Open Jet: 3 m equivalent diameter octagonal jet

 Wind energy, aeronautics, civil engineering Ankara, Turkey High Speed Test Section: Max speed 100 m/s, TI<0.25%

Boundary Layer Test Section: Max speed 30 m/s with spires and roughness elements

Open Jet: Max speed 75 m/s

Interchangeable modular test sections, 6x400 kW axial fan array, 750 kW heat exchanger

References

  1. ↑ "Transonic Wind Tunnel Testing". www.ara.co.uk. Aircraft Research Association. Retrieved 14 September 2019.
  2. ↑ "Boeing: Wind Tunnels and Propulsion Testing Services". www.boeing.com. Retrieved 2017-11-21.
  3. ↑ "Wind tunnel T-101 - Experimental base - TsAGI".
  4. ↑ "Wind tunnel T-105 - Experimental base - TsAGI".
  5. ↑ "JULES VERNE CLIMATIC WIND TUNNEL". CSTB. 2017-10-02.
  6. ↑ "JULES VERNE CLIMATIC WIND TUNNEL". CSTB. 2017-10-02.
  7. ↑ "CSTB Atmospheric Wind Tunnels". CSTB. 2017-10-02.
  8. ↑ "NASA Langley's 30-by-60-Foot Tunnel". nasa.gov. National Aeronautics and Space Administration. Retrieved 10 February 2018.
  9. ↑ "8-Foot High Speed Tunnel". nasa.gov. National Aeronautics and Space Administration. 3 February 2016. Retrieved 10 February 2018.
  10. ↑ Dietrich, Tamara. "NASA Langley dismantles wind tunnel, part of Columbia disaster probe". dailypress.com. Retrieved 2018-07-24.
  11. ↑ Ivanco, Thomas G. (2013-06-24). "Unique Testing Capabilities of the NASA Langley Transonic Dynamics Tunnel, an Exercise in Aeroelastic Scaling". AIAA Ground Testing Conference. Fluid Dynamics and Co-located Conferences. San Diego, CA: American Institute of Aeronautics and Astronautics. doi:10.2514/6.2013-2625. hdl:2060/20140000340.
  12. ↑ ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN Whitfield, Jack D. Dougherty, Jr, N. S. (July 1977). A Survey of Transition Research at AEDC. OCLC 832032113.{{cite book}}: CS1 maint: multiple names: authors list (link)
  13. ↑ "ONERA MODANE WIND TUNNEL". ONERA. 2017-11-16.
  14. ↑ "ONERA MODANE WIND TUNNEL". ONERA. 2017-11-16.
  15. ↑ "Our New State-of-the-Art Facility". RWDI. 2016-12-02.
  16. ↑ "Technical Specification | Boundary Layer and Subsonic Wind Tunnel (BLAST)". blast.utdallas.edu. Retrieved 2022-06-23.
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