List of wind tunnels

Name	Status	Size (W x H x L)	Use	Location	Comments
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
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]
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	Varies		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
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.
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.
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		2.13 m × 2.13 m (7 ft 0 in × 7 ft 0 in)	capable of mach 0.4
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 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
Wind Shear's Full Scale, Rolling Road, Automotive Wind Tunnel			Wind shear	Concord, NC, USA

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. http://www.tsagi.ru/en/experimental_base/wind-tunnel-t-101/
4. http://www.tsagi.ru/en/experimental_base/wind-tunnel-t-105/
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. 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. 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.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.

7. http://www.boeing.com/company/key-orgs/boeing-technology-services/wind-tunnels-and-propulsion.page

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