List of wind tunnels

Last updated

This is an alphabetical list of wind tunnels.

NameStatusSize (W x H x L)UseCountryComments
A2 Wind Tunnel [1] 4 m × 94 m × 18 m
(14 ft × 310 ft × 58 ft)		Full scale general purposeUnited 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 developmentCanadaAvailable and accessible for all industries requiring wind tunnel services or climatic services
Aerodium Sigulda [3] OperationalTesting, training, open to the publicLatviaFirst vertical wind tunnel in Eastern Europe
AeroDyn Wind Tunnel [4] Full scale NASCAR racecarsUnited States
Aerodynamic and Propulsion Test Unit [5] OperationalHypersonicUnited StatesLocated at Arnold Air Force Base and operated by the United States Air Force
Aircraft Research Association [6] Operational2.74 m × 2.44 m × 3.66 m
(9 ft 0 in × 8 ft 0 in × 12 ft 0 in)		TransonicUnited KingdomTransonic 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 cyclingUnited StatesWind 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] Operational2.45 m × 1.55 m × 3.8 m
(8 ft 0 in × 5 ft 1 in × 12 ft 6 in)		Low speed automotive and general purposeSwitzerlandBelt system for rolling road simulation
Boeing Icing Wind Tunnel [10] Operational1 m × 2 m
(4 ft × 6 ft)		United States
Boeing Low-speed Aero-Acoustic Facility [11] OperationalUnited States
Boeing Polysonic (supersonic) Wind Tunnel [12] Operational1 m × 1 m
(4 ft × 4 ft)		United States
Boeing Propulsion Wind Tunnel [13] OperationalLow-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] Operational6 m × 6 m
(20 ft × 20 ft)		United States
Boeing Transonic Wind Tunnel [15] Operational2 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 PurposeUnited States
Building Research Establishment [17] OperationalUnited KingdomTwo 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 industryUnited StatesStartups, major Aerospace corporations and other scientific equipment tested here. Rolling road implementation in progress.
Calspan Wind Tunnel [19] Operational2 m × 2 m
(8 ft × 8 ft)		Subsonic / TransonicUnited StatesThe only independently owned and operated wind tunnel in the United States.
Central Aerohydrodynamic Institute: T-1Diameter 3 m (10 ft)
by 6 m (20 ft)		Russia
Central Aerohydrodynamic Institute: T-2Diameter 6 m (20 ft)
by 14 m (46 ft)		Russia
Central Aerohydrodynamic Institute: T-5Diameter 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-1024 m × 2.33 m × 4 m
(13 ft × 8 ft × 13 ft)		Russia
Central Aerohydrodynamic Institute: T-1034 m × 2.33 m × 3.8 m
(13 ft × 8 ft × 12 ft) (elliptical)		Russia
Central Aerohydrodynamic Institute: T-104Diameter 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-106Diameter 2.7 m (8 ft 10 in)
by 3.5 m (11 ft)		Russia
Central Aerohydrodynamic Institute: T-107Diameter 2.48 m (8 ft 2 in)
by 4.85 m (16 ft)		Russia
Central Aerohydrodynamic Institute: T-1092.5 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-1161 m × 1 m × 2.35 m
(3 ft 3 in × 3 ft 3 in × 7 ft 9 in)		Russia
Central Aerohydrodynamic Institute: T-1172.5 m × 2.4 m × 1.9 m
(8 ft 2 in × 7 ft 10 in × 6 ft 3 in)		Russia
Central Aerohydrodynamic Institute: T-1241 m × 1 m × 4 m
(3 ft 3 in × 3 ft 3 in × 13 ft 1 in)		Russia
Central Aerohydrodynamic Institute: T-1282.75 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] Operational0.91 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 KingdomMach 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] Operational2.4 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] Operational2.4 m (7 ft 10 in) by 1.8 m (5 ft 11 in)United KingdomPart of the UK National Wind Tunnel Facility
Cranfield University Weybridge Wind Tunnel [17] Operational1.067 m (3 ft 6.0 in) diameter jetUnited Kingdom
Cranfield University Icing Tunnel [17] [24] Operational0.76 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 KingdomThree test sections. Part of the UK National Wind Tunnel Facility
CRIACIV Boundary Layer Wind Tunnel - University of Florence [25] Operational2.44 m × 1.6 m × 10 m
(8 ft 0 in × 5 ft 3 in × 32 ft 10 in)		Building, bridges, general purposeItalyClosed circuit wind tunnel, T-shaped diffuser, one atmospheric test section (max speed 31 m/s [100 ft/s]).
Durham University 2m tunnel [17] [26] Operational2 m2 (22 sq ft)United KingdomSubsonic; turbulence generation system; moving or fixed ground
Durham University 1m recirculating wind tunnel [17] [26] Operational0.3 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 Kingdom10 mph (4.5 m/s) – 100 mph (45 m/s)
Durham University – smaller tunnels [17] Operational0.2 m2 (2.2 sq ft)United KingdomThree tunnels; max speed 20 m/s
EDITH supersonic wind tunnel [27] OperationalDiameter 1.2 m (3 ft 11 in)
by 1.7 m (5 ft 7 in)		Long shot time running (20 minutes).FranceFundamental research on shock waves. Aerodynamic and aerothermal behaviour of probes and models. Fluidic thrust vectoring of supersonic nozzle
Energy Technology Centre [17] OperationalWorking section 3.2 m (10 ft) by 3.2 m (10 ft)Wind blade testingUnited 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)		TransonicGermany
Ferrari wind tunnel [29] Operational70 m (230 ft) wide
by 80 m (260 ft) long		Italy
Focke's wind tunnel [30] OperationalGermanyPrivate laboratory of Henrich Focke, not discovered until 1977
Glenn L. Martin Wind Tunnel [31] 3 m × 236 m
(11.04 ft × 775 ft)		Low speed: scale model testing, automotive, aerospaceUnited States
GVPM [32] Operational14 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 purposeItalyVertically 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 StatesLocated at Arnold Air Force Base and operated by the United States Air Force
Imperial College London [17] OperationalLow speed tunnels: 0.4 m2 (4.3 sq ft) to 4.5 m2 (48 sq ft)United KingdomFive low speed tunnels and other tunnels up to mach 9
Jules Verne climatic wind tunnel [34] [35] Operational6 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 purposeFranceThree test sections with wind speeds up to 280 km/h (170 mph)
Klebanoff–Saric Wind Tunnel [36] Operational1.4 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] OperationalDiameter 3 m (10 ft)Vertical, Subsonic, High AOA, Static or body-axis oscillatoryGermanyPrivately 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] Operational7.0 m × 5.0 m × 15.0 m
(23 ft × 16 ft × 49 ft)		Low speed aerospace, full scale automotive and general purposeSwitzerland
Lockheed Martin Low Speed Wind Tunnel [39] Operational8 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 PurposeUnited StatesLarger 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] OperationalUnited KingdomAAE Large Windtunnel
Loughborough University Aeronautical and Automotive Engineering Large Windtunnel [17] OperationalUnited Kingdom
Loughborough University Automotive Wind Tunnel [40] Operational1.92 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] OperationalDiameter 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 < 20FranceFundamental 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
(14 ft × 13 ft × 46 ft)

United StatesClimatic 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 ShockDiameter 406 mm (16 in)Hypersonic propulsionUnited States
NASA Ames Hypersonic Propulsion Integration Direct-ConnectHypersonic propulsionUnited States
NASA Ames National Full Scale Aerodynamic Complex [44] 12 m × 24 m
(40 ft × 80 ft)

24 m × 37 m
(80 ft × 120 ft)

SubsonicUnited StatesLargest wind tunnel in the world
NASA Ames Subsonic 12 Foot High-Rn Pressure [45] Diameter 4 m (12 ft)SubsonicUnited States
NASA Ames 9-by 7-foot Supersonic Wind Tunnel [46] 3 m × 2 m
(9 ft × 7 ft)		SupersonicUnited States
NASA Ames 11-by 11-foot Transonic Wind Tunnel [47] 3 m × 3 m
(11 ft × 11 ft)		TransonicUnited States
NASA Ames Unitary Plan Wind Tunnel [48] Transonic/supersonicUnited States
NASA Glenn 10- by 10-Foot Abe Silverstein Supersonic Wind Tunnel [49] 3 m × 3 m
(10 ft × 10 ft)		SupersonicUnited States
NASA Glenn 8- by 6-Foot Wind Tunnel [50] 2 m × 2 m
(8 ft × 6 ft)		TransonicUnited States
NASA Glenn 9- by 15-Foot Low-Speed Wind Tunnel [51] 3 m × 5 m
(9 ft × 15 ft)		SubsonicUnited States
NASA Glenn Aero-Acoustic Propulsion Laboratory Nozzle Acoustic Test Rig [52] Diameter 1,346 mm (53 in)Acoustic testing of exhaust nozzles, subsonicUnited StatesFree-jet
NASA Glenn Engine Components Research Lab [53] United States
NASA Glenn Hypersonic Test Facility [54] HypersonicUnited States
NASA Glenn Icing Research Tunnel [51] 3 m × 2 m × 6 m
(9 ft × 6 ft × 20 ft)		Subsonic IcingUnited States
NASA Glenn Propulsion Systems Laboratory [55] ActiveDiameter 7 m (24 ft)
by 12 m (38 ft) long		Full-Scale Engine TestingUnited StatesFour 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 atmosphericUnited States
NASA Langley 20-Foot Vertical Spin Tunnel [51] Diameter 6 m (20 ft)Subsonic vertical spinUnited States
NASA Langley Eight-Foot High Speed Tunnel [56] -Diameter 2 m (8 ft)High speedUnited States
NASA Langley Full-Scale Wind Tunnel [57] Demolished9 m × 18 m
(30 ft × 60 ft)		Full-scale aircraftUnited StatesNASA's oldest operating wind tunnel until its closing in October 1995
NASA Langley High-Rn Transonic Dynamics Tunnel [58] Operational5 m × 5 m
(16 ft × 16 ft)		Aeroelasticity, high-risk testing, active controls, rotorcraft performance and stability, transonic aerodynamics.United StatesUnique 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)HypersonicUnited States
NASA Langley Hypersonic 20 Inch Mach 6 Tetrafluoromethane [62] Demolished in 2016 [63] Diameter 508 mm (20 in)HypersonicUnited States
NASA Langley Hypersonic 31 Inch Mach 10 Air [61] Diameter 787 mm (31 in)HypersonicUnited States
NASA Langley Hypersonic Propulsion Integration 15 Inch Mach 6 High-Temperature Tunnel [64] Diameter 381 mm (15 in)HypersonicUnited States
NASA Langley Hypersonic Propulsion Integration 8 Foot High-Temperature Tunnel [65] Diameter 2 m (8 ft)Hypersonic, high-temperatureUnited States
NASA Langley Hypersonic Propulsion Integration Arc-Heated Scramjet [66] HypersonicUnited States
NASA Langley Hypersonic Propulsion Integration Combustion Scramjet [67] HypersonicUnited States
NASA Langley Hypersonic Propulsion Integration Supersonic Combustion [67] HypersonicUnited 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)		TransonicUnited 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 enginesUnited States
NASA Langley Subsonic 12 Foot Atmospheric Lab [71] Diameter 4 m (12 ft)Subsonic atmosphericUnited States
NASA Langley Subsonic Low-Turbulence Pressure Tunnel [72] Subsonic low-turbulenceUnited States
NASA Langley Supersonic High-RnSupersonicUnited States
NASA Langley Transonic 16 Foot Atmospheric [73] 5 m
(16 ft)		Transonic atmosphericUnited States
NASA Langley Variable Density Tunnel [70] Diameter 5 m (15 ft)
by 11 m (34.5 ft) long		Measuring aerodynamic qualities of airfoilsUnited StatesWorld's first variable density wind tunnel
National Wind Tunnel Facility [74] OperationalUnited KingdomTwenty-two wind tunnels at twelve universities allowing open access
ODTÜ-RÜZGEM [75] 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 engineeringTurkey

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] OperationalDiameter 8 m (26 ft)
by 14 m (46 ft)		Subsonic atmosphericFranceLargest continuous blow-down wind tunnel in the world, Mach 0.05 to 1.
ONERA Modane S2MA wind tunnel [77] OperationalSupersonicFranceContinuous-flow wind tunnel, Variable pressure, Mach 0.1 to Mach 3.0.
PHEDRA (Arc-jet) high enthalpy wind tunnel [78] OperationalDiameter 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 mixturesFranceFundamental 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] Operational3.0 m × 2.0 m
(10 ft × 7 ft)		Airfoil aerodynamics and aeroacoustics, 10 to 105 m/s, Re~7MDenmarkNamed for Poul la Cour
Propulsion Wind Tunnel Facility [80] OperationalTransonic: 4.9 m (16 ft)
Supersonic: 4.9 m (16 ft)
Aerodynamic trasonic: 1.2 m (4 ft)		United StatesPart 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] Operational4.9 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

AustriaRTA 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] Operational3.5 m × 2.4 m × 10.5 m
(11 ft × 8 ft × 34 ft)		United KingdomLargest university owned wind tunnel in the United Kingdom, named for R. J. Mitchell
RWDI Wind Tunnels [83] Operational7.32 m
(24 ft)

3.66 m
(12 ft)

Wind engineering, scale buildingsCanadaTwo wind tunnels
San Diego Wind Tunnel [84] 4 m × 2 m × 5 m
(12 ft × 8 ft × 15 ft)		United StatesMajor 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 0-200MPHUnited 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 trucksUnited StatesOpen 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] OperationalLarge 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 studiesCanadaSpeed 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 effectsCanadaSpeed range: 5 to 35 m/s (16 to 115 ft/s)
University of Glasgow [17] OperationalDe-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] OperationalHypersonic 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 KingdomHypersonic wind tunnel: Mach 4, 5, 6; trisonic wind tunnel: Mach 0 to 0.8, 1.8
University of Southampton [17] Operational3' 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] OperationalEnFlo 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)		SubsonicUnited 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 StatesThe 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] OperationalUnited StatesThree tunnels at the Arnold Engineering Development Complex
Williams F1 Wind Tunnel 2 [96] Operational4.4 m × 2.5 m × 12 m
(14 ft × 8 ft × 39 ft)		Motorsport / AutomotiveUnited Kingdom
WindShear Full Scale, Rolling Road, Automotive Wind Tunnel [97] Wind shearUnited States
Windtech Boundary Layer Wind Tunnel [98] Operational3 m × 2 m × 23 m
(10 ft × 7 ft × 75 ft)		Low-Speed / Boundary Layer Wind TunnelAustraliaWindtech 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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The Whitcomb area rule, named after NACA engineer Richard Whitcomb and also called the transonic area rule, is a design procedure used to reduce an aircraft's drag at transonic speeds which occur between about Mach 0.75 and 1.2. For supersonic speeds a different procedure called the supersonic area rule, developed by NACA aerodynamicist Robert Jones, is used.

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<span class="mw-page-title-main">Hypersonic wind tunnel</span>

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References

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