List of wind tunnels

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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.
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:
2.8 m × 2.1 m × 30 m
(9 ft 2 in × 6 ft 11 in × 98 ft 5 in)

Subsonic Test Section:
2.1 m × 2.1 m × 4 m
(6 ft 11 in × 6 ft 11 in × 13 ft 1 in)

Boundary Layer Development / Low-Speed / Subsonic / General Purpose United States
Cal Poly's Low Speed Wind Tunnel[17] 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[18] 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[19] 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[20] 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
CRIACIV Boundary Layer Wind Tunnel - University of Florence[21] 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]).
EDITH supersonic wind tunnel[22] 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
European Transonic Wind Tunnel[23] 2.4 m × 2 m × 9 m
(7 ft 10 in × 6 ft 7 in × 29 ft 6 in) 		Transonic Germany
Ferrari wind tunnel[24] Operational 70 m (230 ft) wide
by 80 m (260 ft) long 		Italy
Focke's wind tunnel[25] Operational Germany Private laboratory of Henrich Focke, not discovered until 1977
Glenn L. Martin Wind Tunnel[26] 3 m × 236 m
(11.04 ft × 775 ft) 		Low speed: scale model testing, automotive, aerospace United States
GVPM[27] Operational 14 m × 3.8 m × 36 m
(46 ft × 12 ft × 118 ft)

4 m × 3.8 m × 4 m
(13 ft × 12 ft × 13 ft)

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[28] Diameter 1.5 m (5 ft) United States Located at Arnold Air Force Base and operated by the United States Air Force
Jules Verne climatic wind tunnel[29][30] Operational 6 m × 5 m × 12 m
(20 ft × 16 ft × 39 ft)

10 m × 7 m × 20 m
(33 ft × 23 ft × 66 ft)

4 m × 2.5 m × 20 m
(13 ft × 8 ft × 66 ft)

Automotive, Rail, Full scale general purpose France Three test sections with wind speeds up to 280 km/h (170 mph)
Klebanoff–Saric Wind Tunnel[31] 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[32] 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.
Large Wind Tunnel Emmen[33] 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[34] Operational 8 m × 9 m × 19 m
(26 ft × 30 ft × 63 ft)

7.0 m × 4.9 m
(23 ft × 16 ft)

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.
MARHy wind Tunnel[35] 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[36] 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)

United States Climatic wind tunnel testing, large truck and automotive
NASA Ames 7-by 10 Foot Wind Tunnel[37] 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[38] 12 m × 24 m
(40 ft × 80 ft)

24 m × 37 m
(80 ft × 120 ft)

Subsonic United States Largest wind tunnel in the world
NASA Ames Subsonic 12 Foot High-Rn Pressure[39] Diameter 4 m (12 ft) Subsonic United States
NASA Ames 9-by 7-foot Supersonic Wind Tunnel[40] 3 m × 2 m
(9 ft × 7 ft) 		Supersonic United States
NASA Ames 11-by 11-foot Transonic Wind Tunnel[41] 3 m × 3 m
(11 ft × 11 ft) 		Transonic United States
NASA Ames Unitary Plan Wind Tunnel[42] Transonic/supersonic United States
NASA Glenn 10- by 10-Foot Abe Silverstein Supersonic Wind Tunnel[43] 3 m × 3 m
(10 ft × 10 ft) 		Supersonic United States
NASA Glenn 8- by 6-Foot Wind Tunnel[44] 2 m × 2 m
(8 ft × 6 ft) 		Transonic United States
NASA Glenn 9- by 15-Foot Low-Speed Wind Tunnel[45] 3 m × 5 m
(9 ft × 15 ft) 		Subsonic United States
NASA Glenn Aero-Acoustic Propulsion Laboratory Nozzle Acoustic Test Rig[46] Diameter 1,346 mm (53 in) Acoustic testing of exhaust nozzles, subsonic United States Free-jet
NASA Glenn Engine Components Research Lab[47] United States
NASA Glenn Hypersonic Test Facility[48] Hypersonic United States
NASA Glenn Icing Research Tunnel[45] 3 m × 2 m × 6 m
(9 ft × 6 ft × 20 ft) 		Subsonic Icing United States
NASA Glenn Propulsion Systems Laboratory[49] 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[45] 4 m × 7 m
(14 ft × 22 ft) 		Subsonic atmospheric United States
NASA Langley 20-Foot Vertical Spin Tunnel[45] Diameter 6 m (20 ft) Subsonic vertical spin United States
NASA Langley Eight-Foot High Speed Tunnel[50]- Diameter 2 m (8 ft) High speed United States
NASA Langley Full-Scale Wind Tunnel[51] 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[52] 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.[53] Good flow quality for large transonic tunnel (Mach 0–1.2)[54]
NASA Langley Hypersonic 20 Inch Mach 6 Air[55] Diameter 508 mm (20 in) Hypersonic United States
NASA Langley Hypersonic 20 Inch Mach 6 Tetrafluoromethane[56] Demolished in 2016[57] Diameter 508 mm (20 in) Hypersonic United States
NASA Langley Hypersonic 31 Inch Mach 10 Air[55] Diameter 787 mm (31 in) Hypersonic United States
NASA Langley Hypersonic Propulsion Integration 15 Inch Mach 6 High-Temperature Tunnel[58] Diameter 381 mm (15 in) Hypersonic United States
NASA Langley Hypersonic Propulsion Integration 8 Foot High-Temperature Tunnel[59] Diameter 2 m (8 ft) Hypersonic, high-temperature United States
NASA Langley Hypersonic Propulsion Integration Arc-Heated Scramjet[60] Hypersonic United States
NASA Langley Hypersonic Propulsion Integration Combustion Scramjet[61] Hypersonic United States
NASA Langley Hypersonic Propulsion Integration Supersonic Combustion[61] Hypersonic United States
NASA Langley NASA / GASL HYPULSE Propulsion Integration[62] United States
NASA Langley National Transonic Facility[63] 2 m × 2 m
(8.2 ft × 8.2 ft) 		Transonic United States
NASA Langley Propeller Research Tunnel[64] 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[65] Diameter 4 m (12 ft) Subsonic atmospheric United States
NASA Langley Subsonic Low-Turbulence Pressure Tunnel[66] Subsonic low-turbulence United States
NASA Langley Supersonic High-Rn Supersonic United States
NASA Langley Transonic 16 Foot Atmospheric[67] 5 m
(16 ft) 		Transonic atmospheric United States
NASA Langley Variable Density Tunnel[64] 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[68] Operational United Kingdom Twenty-two wind tunnels at twelve universities allowing open access
ODTÜ-RÜZGEM[69] Operational

High Speed Test Section:
2.5 m × 2.5 m × 10 m
(8 ft 2 in × 8 ft 2 in × 32 ft 10 in)

Boundary Layer Test Section:
7 m × 3 m × 20 m
(23 ft × 10 ft × 66 ft)

Open Jet:
3 m (10 ft)
equivalent diameter octagonal 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[70] 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[71] Operational Supersonic France Continuous-flow wind tunnel, Variable pressure, Mach 0.1 to Mach 3.0.
PHEDRA (Arc-jet) high enthalpy wind tunnel[72] 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[73] 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[74] 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[75] 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[76] 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[77] Operational 7.32 m
(24 ft)

3.66 m
(12 ft)

Wind engineering, scale buildings Canada Two wind tunnels
San Diego Wind Tunnel[78] 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[79] Brazil
Texas A&M Oran W. Nicks Low Speed Wind Tunnel[80] 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[81] 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[82] 3,912 mm × 356 mm
(154 in × 14 in) 		United States
Trudelturm[83] Height 20 m (66 ft) Germany
University of British Columbia Boundary Layer Wind Tunnel[84] 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[85] 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 Washington Aeronautical Laboratory, Kirsten Wind Tunnel[86] 2 m × 4 m × 3 m
(8 ft × 12 ft × 10 ft) 		Subsonic United States
University of Washington Department of Aeronautics & Astronautics 3x3[87] 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[88] 2 m × 2 m
(6 ft × 6 ft) 		United States
Von Karman Gas Dynamics Facility[89] Operational United States Three tunnels at the Arnold Engineering Development Complex
Williams F1 Wind Tunnel 2[90] 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[91] Wind shear United States
Windtech Boundary Layer Wind Tunnel[92] 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)

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  52. ^ "Transonic Dynamics Tunnel". Retrieved 26 January 2024.
  53. ^ Ivanco, Thomas G. (24 June 2013). "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. Retrieved 26 January 2024.
  54. ^ Arnold Engineering Development Center Arnold AFS TN (July 1977). "Unknown". A Survey of Transition Research at AEDC. By Whitfield, Jack D.; Dougherty, Jr, N. S. OCLC 832032113.
  55. ^ a b "NASA Langley Aerothermodynamics Laboratory: Hypersonic Testing Capabilities" (PDF). Retrieved 26 January 2024.
  56. ^ "Taking Apart a Wind Tunnel". Retrieved 26 January 2024.
  57. ^ Dietrich, Tamara. "NASA Langley dismantles wind tunnel, part of Columbia disaster probe". dailypress.com. Retrieved 24 July 2018.
  58. ^ Hodge, Jeffery (17 August 2012). "The Langley 15-inch Mach 6 High Temperature Tunnel". doi:10.2514/6.1992-3938. Retrieved 26 January 2024.
  59. ^ "8-Foot High Temperature Tunnel (HTT)". Retrieved 26 January 2024.
  60. ^ "Current Test Capabilities of NASA Langley's Arc-Heated Scramjet Test Facility" (PDF). Retrieved 26 January 2024.
  61. ^ a b "The NASA Langley Scramjet Test Complex" (PDF). Retrieved 26 January 2024.
  62. ^ "NASA's HYPULSE Facility at GASL A Dual Mode, Dual Driver Reflected-Shock/Expansion Tunnel". Retrieved 26 January 2024.
  63. ^ "National Transonic Facility". Retrieved 26 January 2024.
  64. ^ a b "100 Years of Rocketry and Research at NASA's Langley Facility". Retrieved 26 January 2024.
  65. ^ "12 Foot Low-Speed Tunnel (12 FT LST)". Retrieved 26 January 2024.
  66. ^ "Low Turbulence Pressure Tunnel (Building 582A)". Retrieved 26 January 2024.
  67. ^ "16-Foot Transonic Tunnel (Building 1146)". Retrieved 26 January 2024.
  68. ^ "National Wind Tunnel Facility". Retrieved 27 January 2024.
  69. ^ "ODTÜ-RÜZGEM Large Scale Wind Tunnel at The Middle East Technical University (METU)". Retrieved 26 January 2024.
  70. ^ "ONERA Mondane Wind Tunnel". ONERA. 16 November 2017. Retrieved 26 January 2024.
  71. ^ "S2MA Continuous-flow wind tunnel, Variable pressure, Mach 0.1 to Mach 3.0". ONERA.
  72. ^ "-PHEDRA- Institut de Combustion Aérothermique Réactivité et Environnement". Retrieved 26 January 2024.
  73. ^ "Poul la Cour Tunnel (PLCT)". Retrieved 26 January 2024.
  74. ^ "Propulsion Wind Tunnel Facility". Retrieved 27 January 2024.
  75. ^ "Rail Tec Arsenal Climatic Wind Tunnel". Retrieved 26 January 2024.
  76. ^ "R J Mitchell Wind Tunnel". Retrieved 27 January 2024.
  77. ^ "RWDI's Wind Tunnels and Model Shop". RWDI. Retrieved 26 January 2024.
  78. ^ "San Diego Wind Tunnel". Retrieved 26 January 2024.
  79. ^ "Tunel de vento hipersônico T3 entra em fase de qualificação" (PDF) (in Portuguese). IEAv. Archived from the original (PDF) on 6 July 2011. Retrieved 18 January 2011.
  80. ^ "Texas A&M University Oran W. Nicks Low-Speed Wind Tunnel (TAMU LSWT)". Retrieved 26 January 2024.
  81. ^ "Vehicle Climatic Wind Tunnel". Retrieved 26 January 2024.
  82. ^ "The George C. Marshall Space Flight Center's 14 x 14-Inch Trisonic Wind Tunnel - A historical perspective". Retrieved 26 January 2024.
  83. ^ "Deutsche Versuchsanstalt für Luftfahrt (DVL)" (in German). Retrieved 27 January 2024.
  84. ^ "University of British Columbia Boundary Layer Wind Tunnel". Retrieved 26 January 2024.
  85. ^ "University of British Columbia Parkinson Wind Tunnel". Retrieved 26 January 2024.
  86. ^ "Kirsten Wind Tunnel (KWT)". Retrieved 26 January 2024.
  87. ^ "3x3 Low-Speed Wind Tunnel". Retrieved 26 January 2024.
  88. ^ "Virginia Tech Stability Wind Tunnel". Retrieved 26 January 2024.
  89. ^ "The von Karman Gas Dynamics Facility Wind Tunnels". Retrieved 27 January 2024.
  90. ^ Noble, Jonathan (13 June 2011). "Team Lotus signs Williams tunnel deal". Retrieved 26 January 2024.
  91. ^ "Windshear". Retrieved 26 January 2024.
  92. ^ "Windtech Boundary Layer Wind Tunnel". Retrieved 26 January 2024.
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