wind tunnel connection

The information below is old and needs to be updated but we don't want to lose the data so it is being stored here until Mike retires. If you really must send us an update, send it to windtunnels@worthey.net and the information will be saved for him.
Last modified on 05 August, 2000. THIS SITE IS UNDER RENOVATION Thanks for your patience as we update our data. Welcome to The Wind Tunnel Connection This website has been established as an informational tool for aerospace professionals. Our goal is to build a site containing useful information for engineers engaged in the design, testing and fabrication of aerospace vehicles, hardware and software. As we build this website please feel free to make suggestions. We hope that the information in this site proves useful. Our Sponsors This website has been made possible through the support of : [Currently we have no sponsors. See Sponsorhsip link on the left for info on becoming a sponsor.] Wind Tunnels We are currently building the most complete up-to-date database of wind tunnels in the country. Our goal is to list every site in the world. We will add and update information on the various facilities as fast as we can. If we leave one out or you have more up-to-date information please let us know. Any information that will improve the data contained in this site will be most appreciated. Please keep in mind, this website is being updated on a continuous basis. Related Aerospace Resources Besides our wind tunnel listings, we have included links to online technical documents from NASA, the US Department of Defense, and many others. We also publish a quarterly newsletter. Previous issues are posted on this website and are available for download. The Wind Tunnel Connection relies on its user community to help us improve. If you have any suggestions as to how we can improve this website please let us know. Contact Information Telephone Electronic mail Webmaster: webmaster@worthey.net Thanks for coming by and we hope you come back soon to see our progress. This site has had visits since 01 January 2001. Subsonic Wind Tunnels National Aeronautics & Space Administration NASA Ames Research Center NASA Langley Research Center NASA Glenn Research Center United States Department of Defense US Air Force Research Laboratories US Army Aeromechanics Laboratory Naval Surface Warfare Center, Carderock Division U. S. Aerospace Industry The Boeing Company Lockheed Martin Corporation Allied Aerospace Industries - MicroCraft Northrop Grumman Corporation United Technologies U.S. Universities Georgia Institute of Technology Massachusetts Institute of Technology University of Maryland Old Dominion University Texas A&M University University of Washington Virginia Polytechnic Institute Wichita State University International Installations Canada National Research Council, Institute for Aerospace Research Belgium Von Karman Institute for Fluid Dynamics France Onera Germany DNW German-Dutch Wind Tunnels India Indian Institute of Science National Aerospace Laboratories Indian Institute of Technology Kanpur Russia Central Aerohydrodynamic Institute TsAGI Institute of Theoretical and Applied Mechanics Sweden FOI - Swedish Defence Research Agency United Kingdom Flow Science - Goldstein Research Laboratory Imperial College DERA University of Glasgow National Aeronautics & Space Administration NASA Ames Research Center Wind Tunnel Test Section (ft) Speed Range (Mach No.) Reynolds No. (per ft x 106) 80 X 120 ft 80 x 1200 to 100 kts 0 - 1.2 40 X 80 ft 40 x 80 x 800 to 300 kts 0 - 3 12 ft Pressure Tunnel 11.3 x 11.3 x 280 .05 - 0.55 0.1 - 12 NASA Langley Research Center Wind Tunnel Test Section (ft) Speed Range (Mach No.) Reynolds No. (per ft x 106) 14 X 22 Foot Subsonic Tunnel 14.5 x 21.75 x 50 0 to 0.3 0 to 2.1 12 foot Low Speed Tunnel 12 ft x 15 ft 0 to 77 ft/sec 0 to 0.5 Low-Turbulence Pressure Tunnel (LTPT) 7.5 x 3 x 7.5 0.05 - 0.5 0.4 - 15. 20-foot Vertical Spin Tunnel 20 dia, 25 H0 to 85 ft/sec 0.0 to 0.15 NASA Glenn Research Center Wind Tunnel Test Section (ft) Speed Range (Mach No.) Reynolds No. (per ft x 106) 9 X 15 ft 9 x 15 0 - 0.2 0 - 1.4 Icing Research Tunnel (IRT) 6 x 9 0 - 0.5 3.3 U.S. Department of Defense US Air Force Research Laboratories Wind Tunnel Facility Test Section (ft) Speed Range (Mach No.) Reynolds No. (per ft x 106) SARL 10 x 7 0.20 - 0.50 Vertical Wind Tunnel 12 x 15 0 - 150 ft/sec 0 - 0.91 Naval Surface Warfare Center, Carderock Division Wind Tunnel Facility Test Section (ft) Speed Range (Mach No.) Reynolds No. (per ft x 106) Subsonic 8 x 10 20 - 275 ft/sec1.75 US Army Aeromechanics Laboratory Wind Tunnel Facility Test Section (ft) Speed Range (Mach No.) Reynolds No. (per ft x 106) Army Aeromechanics Laboratory (NASA Ames) 7 x 10 0 - 0.33 0 - 2.1 U.S. Industry The Boeing Company Wind Tunnel Test Section (ft) Speed Range (Mach No.) Reynolds No. (per ft x 106) 20 X 20 20 x 20 0 - 215 knots 0 - 100 knots (open-jet) 0 - 2.3 BRAIT 5 x 8 4 x 6 (w/inserts) 0 - 150 knots (5x8) 0 - 250 knots (4x6) 9 x 9 Subsonic Propulsion Tunnel 9 x 9 0 - 200 knots Lockheed Martin Wind Tunnel Test Section (ft) Speed Range (Mach No.) Reynolds No. (per ft x 106) LSWT # 1 & 2 30 x 26 (#1) 14 -146 FT/SEC (#1) 0 - 1 16 x 23 (#2) 29 - 293 ft/sec (#2) 0 - 2 8 X 128 x 12 0 - 293 ft/sec 0 - 1.7 IWT4 x 2.5 88 - 308 ft/sec 0 - 2 Allied Aerospace Industries - Micro Craft Wind Tunnel Test Section (ft) Speed Range (Mach No.) Reynolds No. (per ft x 106) LSWT 8 x 12 0 - 0.37 0 - 2.5 Northrop Grumman Wind Tunnel Test Section (ft) Speed Range (Mach No.) Reynolds No. (per ft x 106) Research 2.5 x 3.5Max Q = 60 psf1.7 7 X 10 7 x 10 Mach = 0 to 0.361.8 United Technologies Wind TunnelTest Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Large Subsonic WT 8' Octogonal x 16' long 10 x 15 x 31 18' Octogonal x 40' long Mach = 0 to 0.90 Mach = 0 to 0.45 Mach = 0 to 0.264.5 2.6 1.6 Acoustic Research Tunnel5' Diameter 50" Diameter x 8' longUp to Mach = 0.65 Up to Mach = 0.354.6 4.6 Pilot Wind Tunnel 4 x 6 x 8Mach = 0.120.90 University Facilities Georgia Institute of Technology Wind TunnelTest Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) 7 X 9 ft 7 x 90 - 0.220 - 1.6 Low Turbulence 3.5 x 3.573 ft/sec0.5 Massachusetts Institute of Technology Wind TunnelTest Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Wright Brothers 7.5 x 10 EllipticalUp to 0.36 @ 0.25 barUp to 2.25 @ 1.5 bar Return University of Maryland Wind TunnelTest Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Glenn L. Martin 7.75 x 11.040.0 - 0.3N/A Old Dominion University Wind TunnelTest Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Langley Full Scale Tunnel 30 x 6038 - 132 ft/sec1 Return Texas A&M University Wind TunnelTest Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) 7 X 10 ft 7 x 100 - 0.250 - 1.9 Virginia Polytechnic Institute Wind TunnelTest Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Stability Wind Tunnel 6 x 60 - 275 ft/sec1.5 University of Washington Wind TunnelTest Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Kirsten Wind Tunnel 8 x 120 - 302 ft/sec0 - 1.8 Return Wichita State University Wind TunnelTest Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Beech Wind Tunnel 7 x 100 - 264 ft/sec0 - 1.5 International Installations Belgium Von Karman Institute for Fluid Dynamics Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. Cold wind tunnel CWT-1 rectangular test section with 0.1 m x 0.3 m cross section and 1.6 m length0 - 65 m/s Cryogenic wind tunnel T'3 10 cm x 8 cm 0 - 90 m/s L-1A 3 m diameter2 to 60 m/s L-2A octagonal test section of 0.28 m width and 1.3 m length0 - 45 m/s L-7 0.16 m x 0.16 m cross section 0 - 20 m/s L-7+ 0.36 m x 0.27 m 0 - 15 m/s Canada National Research Council, Institute for Aerospace Research Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. 9m x 9m Low Speed Wind Tunnel 9.1m x 9.1m x 22.9m0 to 55 m/s 2.3m x 3m Wind Tunnel 1.9m x 2.7m x 5.2m140 m/s 5m Vertical Wind Tunnel 5m dia open jet 3m x 3m square open jet 2m x 3m open jet or solid wall28 m/s Altitude Icing Tunnel 57cm x 57cm x 183cm5 to 100 m/s 0.9 m pilot wind tunnel 0.9m x 0.9m x 2.3m0.3 to 40 m/s France Onera Wind TunnelTest Section (m)Speed Range (Mach No.)Reynolds No. F1 4.5 x 3.5 x 110.05 - 0.368x106 F2 1.8 x 1.4 x 50 - 105 m/sec1.1x106 Germany / Netherlands DNW - German-Dutch Wind Tunnels Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x106) LST Low Speed Tunnel 3 x 2.50 - 0.231.4 NWB 3.25 x 2.80 - 0.26 (0 - 0.22 open)1.8 LLF Large Low Speed Facility 6 x 6 8 x 6 9.5 x 9.50 - 152 m/s 0 - 116 m/s 0 - 62 m/s6 5.3 3.9 Cryogenic wind tunnel Cologne (KKK) 2.4 m x 2.4 m up to 0.38 9.5 HDG High Pressure Wind Tunnel 0.6 x 0.6 closed 0.6 x 0.4 closed 0.6 x 0.4 open2 - 35 m/s 12 India Indian Institute of Science Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x106/m) Open Circuit LSWT9 x 14 ftupto 55 m/s3 National Aerospace Laboratories Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x106/m) Low speed wind tunnel1.5 x 1.5 mupto 60 m/s3 Indian Institute of Technology Kanpur Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x106/m) National Wind Tunnel Facility 3 x 2.25 mupto 80 m/s6 Russia Central Aerohydrodynamic Institute TsAGI Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per m x 106) T 101 24 x 14 x 24 elliptical5 - 55 m/secup to 3.3 T 102 4 x 2.33 elliptical5 - 55 m/secup to 3.3 T 103 2.33 x 4 elliptical5 - 110 m/secup to 7 T 104 7 round15 - 125 m/secup to 8 T 30 1.2 round10 - 65 m/secup to 4 Institute of Theoretical and Applied Mechanics Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per m x 106) T-324 (CC) 1 x 10.03 - 0.33 Sweden FOI - Swedish Defence Research Agency Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per meter) LT1 3.6 dia0 - 80 m/s United Kingdom - Great Britain Flow Science - Goldstein Research Laboratory Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per meter) 0.5m x 0.5m Low Turbulence Tunnel 0.5 m x 0.5 m square cross section by 3.0 m long42 m/s 1.35m x 0.95m Blow Down Tunnel 1.35 m x 0.95 m cross section with corner fillets by 2.0 m long50m/s Avro' 2.7m x 2.2m (9' x 7') Low Speed Closed return Tunnel 2.75 m x 2.23 m octagonal cross section by 5.5 m long70 m/s 4.5m x 1.5m (15' x 5') Environmental Wind Tunnel 4.57 m x 1.52 m rectangular cross section by 9.14 m long20 m/s Imperial College Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per meter) 10 x 5 Honda Wind Tunnel 3 x 1.5up to 35 m/sec Donald Campbell General Purpose Low Speed Wind Tunnel 1.37 x 1.22 Low Speed Wind-Tunnel 0.9 x 0.9 Flow Visualisation Tunnel 2 x 0.6 DERA Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per meter) 5m Pressurized Low Speed 5m dia 1 3ft x 9ft Atmospheric Low Speed 13ft x 9ft boundary Layer Tunnel up to 45 m/s 4ft x 3ft Low Speed Tunnel 4ft x 3ftup to 30 m/s University of Glasgow Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per meter) Argyll Wind Tunnel 2.65 x 2.040 to 76 m/s Handly-Page Wind Tunnel 2.13 x 1.610 to 60 m/s The 1.15 x 0.95 Low Speed Wind Tunnel 1.15 x 0.950 to 30 m/s Flow Visualisation Wind Tunnel 0.9 x 0.90 to 5 m/s Return National Aeronautics & Space Administration NASA Ames Research Center Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) 80 X 120 ft 80 x 1200 to 100 kts0 - 1.2 40 X 80 ft 40 x 80 x 800 to 300 kts 0 - 3 12 ft Pressure Tunnel 11.3 x 11.3 x 280.05 - 0.55 0.1 - 12 NASA Langley Research Center Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) 14 X 22 Foot Subsonic Tunnel 14.5 x 21.75 x 500 to 0.30 to 2.1 12 foot Low Speed Tunnel12 ft x 15 ft0 to 77 ft/sec0 to 0.5 Low-Turbulence Pressure Tunnel (LTPT) 7.5 x 3 x 7.50.05 - 0.50.4 - 15. 20-foot Vertical Spin Tunnel 20 dia, 25 H0 to 85 ft/sec0.0 to 0.15 NASA Glenn Research Center Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) 9 X 15 ft 9 x 150 - 0.20 - 1.4 Icing Research Tunnel (IRT) 6 x 90 - 0.53.3 U.S. Department of Defense US Air Force Research Laboratories Wind Tunnel Facility Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) SARL 10 x 70.20 - 0.50 Vertical Wind Tunnel 12 x 150 - 150 ft/sec0 - 0.91 Naval Surface Warfare Center, Carderock Division Wind Tunnel Facility Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Subsonic 8 x 1020 - 275 ft/sec1.75 US Army Aeromechanics Laboratory Wind Tunnel Facility Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Army Aeromechanics Laboratory (NASA Ames)7 x 100 - 0.330 - 2.1 U.S. Industry The Boeing Company Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) 20 X 20 20 x 200 - 215 knots 0 - 100 knots (open-jet)0 - 2.3 BRAIT 5 x 8 4 x 6 (w/inserts)0 - 150 knots (5x8) 0 - 250 knots (4x6) 9 x 9 Subsonic Propulsion Tunnel 9 x 90 - 200 knots Lockheed Martin Wind TunnelTest Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) LSWT # 1 & 2 30 x 26 (#1) 16 x 23 (#2)14 -146 ft/sec (#1) 29 - 293 ft/sec (#2)0 - 1 0 - 2 8 X 128 x 120 - 293 ft/sec0 - 1.7 IWT4 x 2.588 - 308 ft/sec0 - 2 Allied Aerospace Industries - Micro Craft Wind TunnelTest Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) LSWT 8 x 120 - 0.370 - 2.5 Return Northrop Grumman Wind TunnelTest Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Research 2.5 x 3.5Max Q = 60 psf1.7 7 X 10 7 x 10Mach = 0 to 0.361.8 United Technologies Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Large Subsonic WT 8' Octogonal x 16' long 10 x 15 x 31 18' Octogonal x 40' long Mach = 0 to 0.90 Mach = 0 to 0.45 Mach = 0 to 0.264.5 2.6 1.6 Acoustic Research Tunnel5' Diameter 50" Diameter x 8' longUp to Mach = 0.65 Up to Mach = 0.354.6 4.6 Pilot Wind Tunnel 4 x 6 x 8Mach = 0.120.90 University Facilities Georgia Institute of Technology Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) 7 X 9 ft 7 x 90 - 0.220 - 1.6 Low Turbulence 3.5 x 3.573 ft/sec0.5 Massachusetts Institute of Technology Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Wright Brothers 7.5 x 10 EllipticalUp to 0.36 @ 0.25 barUp to 2.25 @ 1.5 bar University of Maryland Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Glenn L. Martin 7.75 x 11.040.0 - 0.3N/A Old Dominion University Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Langley Full Scale Tunnel 30 x 6038 - 132 ft/sec1 Texas A&M University Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) 7 X 10 ft 7 x 100 - 0.250 - 1.9 Virginia Polytechnic Institute Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Stability Wind Tunnel 6 x 60 - 275 ft/sec1.5 University of Washington Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Kirsten Wind Tunnel 8 x 120 - 302 ft/sec0 - 1.8 Wichita State University Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Beech Wind Tunnel 7 x 100 - 264 ft/sec0 - 1.5 International Installations Belgium Von Karman Institute for Fluid Dynamics Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. Cold wind tunnel CWT-1 rectangular test section with 0.1 m x 0.3 m cross section and 1.6 m length0 - 65 m/s Cryogenic wind tunnel T'3 10 cm x 8 cm 0 - 90 m/s L-1A 3 m diameter2 to 60 m/s L-2A octagonal test section of 0.28 m width and 1.3 m length0 - 45 m/s L-7 0.16 m x 0.16 m cross section 0 - 20 m/s L-7+ 0.36 m x 0.27 m 0 - 15 m/s Canada National Research Council, Institute for Aerospace Research Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. 9m x 9m Low Speed Wind Tunnel 9.1m x 9.1m x 22.9m0 to 55 m/s 2.3m x 3m Wind Tunnel 1.9m x 2.7m x 5.2m140 m/s 5m Vertical Wind Tunnel 5m dia open jet 3m x 3m square open jet 2m x 3m open jet or solid wall28 m/s Altitude Icing Tunnel 57cm x 57cm x 183cm5 to 100 m/s 0.9 m pilot wind tunnel 0.9m x 0.9m x 2.3m0.3 to 40 m/s France Onera Wind TunnelTest Section (m)Speed Range (Mach No.)Reynolds No. F1 4.5 x 3.5 x 110.05 - 0.368x106 F2 1.8 x 1.4 x 50 - 105 m/sec1.1x106 Germany / Netherlands DNW - German-Dutch Wind Tunnels Wind TunnelTest Section (m)Speed Range (Mach No.)Reynolds No. (x106) LST Low Speed Tunnel 3 x 2.50 - 0.231.4 NWB 3.25 x 2.80 - 0.26 (0 - 0.22 open)1.8 LLF Large Low Speed Facility 6 x 6 8 x 6 9.5 x 9.50 - 152 m/s 0 - 116 m/s 0 - 62 m/s6 5.3 3.9 Cryogenic wind tunnel Cologne (KKK) 2.4 m x 2.4 m up to 0.38 9.5 HDG High Pressure Wind Tunnel 0.6 x 0.6 closed 0.6 x 0.4 closed 0.6 x 0.4 open2 - 35 m/s 12 India Indian Institute of Science Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x106/m) Open Circuit LSWT9 x 14 ftupto 55 m/s3 National Aerospace Laboratories Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x106/m) Low speed wind tunnel1.5 x 1.5 mupto 60 m/s3 Indian Institute of Technology Kanpur Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x106/m) National Wind Tunnel Facility 3 x 2.25 mupto 80 m/s6 Russia Central Aerohydrodynamic Institute TsAGI Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per m x 106) T 101 24 x 14 x 24 elliptical5 - 55 m/secup to 3.3 T 102 4 x 2.33 elliptical5 - 55 m/secup to 3.3 T 103 2.33 x 4 elliptical5 - 110 m/secup to 7 T 104 7 round15 - 125 m/secup to 8 T 30 1.2 round10 - 65 m/secup to 4 Institute of Theoretical and Applied Mechanics Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per m x 106) T-324 (CC) 1 x 10.03 - 0.33 Sweden FOI - Swedish Defence Research Agency Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per meter) LT1 3.6 dia0 - 80 m/s United Kingdom - Great Britain Flow Science - Goldstein Research Laboratory Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per meter) 0.5m x 0.5m Low Turbulence Tunnel 0.5 m x 0.5 m square cross section by 3.0 m long42 m/s 1.35m x 0.95m Blow Down Tunnel 1.35 m x 0.95 m cross section with corner fillets by 2.0 m long50m/s Avro' 2.7m x 2.2m (9' x 7') Low Speed Closed return Tunnel 2.75 m x 2.23 m octagonal cross section by 5.5 m long70 m/s 4.5m x 1.5m (15' x 5') Environmental Wind Tunnel 4.57 m x 1.52 m rectangular cross section by 9.14 m long20 m/s Imperial College Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per meter) 10 x 5 Honda Wind Tunnel 3 x 1.5up to 35 m/sec Donald Campbell General Purpose Low Speed Wind Tunnel 1.37 x 1.22 Low Speed Wind-Tunnel 0.9 x 0.9 Flow Visualisation Tunnel 2 x 0.6 DERA Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per meter) 5m Pressurized Low Speed 5m dia 13ft x 9ft Atmospheric Low Speed 13ft x 9ft boundary Layer Tunnel up to 45 m/s 4ft x 3ft Low Speed Tunnel 4ft x 3ftup to 30 m/s University of Glasgow Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per meter) Argyll Wind Tunnel 2.65 x 2.040 to 76 m/s Handly-Page Wind Tunnel 2.13 x 1.610 to 60 m/s The 1.15 x 0.95 Low Speed Wind Tunnel 1.15 x 0.950 to 30 m/s Flow Visualisation Wind Tunnel 0.9 x 0.90 to 5 m/s Transonic Wind Tunnels National Aeronautics & Space Administration NASA Ames Research Center NASA Langley Research Center NASA Marshall Space Flight Center United States Department of Defense US Air Force Arnold Engineering Development Center U.S. Aerospace Industry Boeing Aero Systems Engineering Lockheed Martin Allied Aerospace Industries - MicroCraft Verdian - Calspan Operation International Installations Australia Defense Science and Technology Organization Canada National Research Council, Institute for Aerospace Research Belgium Von Karman Institute for Fluid Dynamics France Onera Germany DNW - German-Dutch Wind Tunnels DLR - German Aerospace Center India National Aerospace Laboratories Japan Netherlands DNW- German-Dutch Wind Tunnels (NLR) Russia Central Aerohydrodynamic Institute TsAGI Institute of Theoretical and Applied Mechanics Sweden FOI - Swedish Defence Research Agency United Kingdom Flow Science - Goldstein Research Laboratory Aircraft Research Association DERA National Aeronautics & Space Administation NASA Ames Research Center Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) 11 - ft (Unitary) 11 x 11 x 220.20 - 1.50 0.3 - 9.6 NASA Langley Research Center Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) 16-ft Transonic Tunnel 15.5 x 15.50.2 - 1.251. to 4. 0.3M Transonic Cryogenic Tunnel 8 x 24 in0.2 - 0.91 to 100 National Transonic Facility 8.2 x 8.20.1 - 1.24 to 146 Transonic Dynamics Tunnel (TDT) 16 x 160.1 - 1.20.03 to 3 (Air) 0.2 to 10 (R-134a) NASA Marshall Space Flight Center Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) High Re32 in dia0.30 - 3.507 - 200 U. S. Department of Defense US Air Force Arnold Engineering Development Center Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Propulsion Wind Tunnel Facility 16T 4T 16 x 16 4 x 4 0.0 - 1.6 0.1 - 1.3, 1.6, 2.0 0.1 - 6.0 2.0 - 6.0 @ M = 1.6 1.3 - 6.1 @ M = 2.0 U. S. Aerospace Industry The Boeing Company Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) BTWT 8 x 120 - 1.150 - 4 Polysonic 4 x 40.20 - 5.84 - 50 Aero Systems Engineering Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) 22-in 22 x 22 in0 - 1.15 66-in 66 x 66 in0 - 1.00 - 4.5 Lockheed Martin Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) HSWT 4 x 40.4 - 4.84 - 34 Allied Aerospace Industries - MicroCraft Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Tri-Sonic 7 x 7 ft0.1 - 3.52 - 19 Veridian - Calspan Operations Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Calspan 8 x 8 ft0 - 1.35 0 - 12.5 International Wind Tunnels Australia australia Defense Science and Technology Organization Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. Transonic wind tunnel 0.806 m x 0.806 m0.3 – 1.2, continuously variable. 1.4 with replaceable nozzle Belgium Von Karman Institute for Fluid Dynamics Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. Transonic/supersonic wind tunnel S-1 40 cm x 40 cm 0.4 to 1.05, 1.43 2.0 and 2.25 4 x 106 /m Canada National Research Council, Institute for Aerospace Research Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. Pilot Blowdown Wind Tunnel 1/12 scale of 1.5m Blowdown 1.5m Transonic Blowdown Wind Tunnel 1.5m x 1.5m0.1 to 0.75 subsonic 0.7 to 1.4 transonic 1.1 to 4.25 supersonic France Onera Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x 106) S1Ma 6.74 x 6.27(6.85) 8 m dia0.05 - 1.07.9 S2Ma 1.75 x 1.77 0.1 - 1.35.4 S3Ma 0.56 x 0.780.1 - 1.33.5 Germany DLR - German Aerospace Center Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x107)/m VMK Vertical Test Section Nozzel exit dia 150, 230, and 310 mm0.4 - 0.9, 1.57 - 3.225 TMK Trisonic Wind Tunnel 60 x 60 cm0.5 - 5.70.7 to 7 DNW - German-Dutch Wind Tunnels Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x106) TWG Transonic Wind Tunnel 1 x 10.3 < M < 0.9 (Subsonic Test Section) (0.5) - 0.85 < M < 1.2, (Transonic Test Section) 1.33 < M < 2.21 (Supersonic Test Section) 1.8 KRG - Cryogenic Ludwieg-Tube cross section of 0.4 x 0.35² and a length of 2 m0.30 < M < 0.95 78 India india National Aerospace Laboratories Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x 106) 1.2m Trisonic Tunnel (H1) 1.2 x 1.20.20 - 4.0 0.6m Transonic Tunnel (H2) 0.6 x 0.60.20 - 1.2 Netherlands DNW - German-Dutch Wind Tunnels Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x 106) CSST - Continuous Supersonic Tunnel 0.27 x 0.27M = 0.3 - 44 HST rectangular cross section 2.00 x 1.60 or 1.80 M = 0 to 1.35 9 Russia russia Central Aerohydrodynamic Institute TsAGI Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per m x 106) T-106 2.48 dia0.15 - 1.135 T-108 1 x 10.2 - 1.711 - 20 T-109 2.25 x 2.250.4 - 460 TPD 4 dia0.3 - 460 SVS-1 0.09, 0.16, 0.22 roundup to 2.0 SVS-2 0.5 x 0.516, 0.56 round0.3 - 6.0110 T-112 0.6 x 0.60.6 - 1.815 T-114 0.6 x 0.60.3 - 420 T-115 0.15 x 0.200.2 - 1.2, 2, 3, 43.8 T-128 2.75 x 2.750.15 - 1.741 Institute of Theoretical and Applied Mechanics Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per m x 106) T-325 (BD) 0.2 x 0.20.5 - 420 Sweden FOI - Swedish Defence Research Agency Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. T1500 4 x 1.5 x 1.50.20 to 1.25, with slotted walls or 0.20 to 0.80 and 1.3 to 2.0, with solid wallsUp to 80 million/m S4 (transonic): 0.92 x 0.90 (supersonic): 0.90 x 1.15 0.5 - 2.0 800,000 - 1,600,000 /m S5 (transonic): 0.46 x 0.48 (supersonic): 0.46 x 0.570.5 - 3.6400,000 - 800,000 /m United Kingdom - Great Britain Flow Science - Goldstein Research Laboratory Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. 0.21m x 0.15m Transonic / Supersonic Wind Tunnel 0.21 m x 0.15 m rectangular cross section with slotted walls by 0.6 m longMach 0.3 to Mach 0.9 Aircraft Research Association Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per m) Transonic Wind Tunnel (TWT) 2.74 x 2.440.2 - 1.4 Two Dimensional Tunnel (2DT) 203 mm x 475 mm0.3 - 0.87 Small Transonic Wind Tunnel (Z4T) 0.23 x 0.200.3 - 1.315 x 106 DERA Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per meter) 8 x 8 Pressurized High Speed 8ft x 8ft Supersonic Wind Tunnels National Aeronautics & Space Administration NASA Ames Research Center NASA Langley Research Center NASA Glenn Research Center United States Department of Defense United States Air Force U.S. Aerospace Industry Boeing Lockheed - Martin Aero Systems Engineering Allied Aerospace Industries - MicroCraft Verdian - Calspan Operation Calspan - University of Buffalo Research Center (CUBRC) International Installations Canada Belgium Von Karman Institute for Fluid Dynamics France Onera Germany DNW - German-Dutch Wind Tunnels DLR - German Aerospace Center India National Aerospace Laboratories Japan Netherlands DNW - German-Dutch Wind Tunnels (NLR) Russia Central Aerohydrodynamic Institute TsAGI Institute of Theoretical and Applied Mechanics Sweden FOI - Swedish Defence Research Agency United Kingdom Flow Science - Goldstein Research Laboratory DERA Aircraft Research Association National Aeronautics & Space Administration NASA Ames Research Center Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) 9 x 7 (Unitary) 9 x 7 x 181.55 - 2.5 1.0 to 6.0 NASA Langley Research Center Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Unitary Plan Wind Tunnel 4 x 4 x71.5 to 2.9 2.3 to 4.60.5 to 6 0.5 to 11 Supersonic Low Disturbance Tunnel 6 in x 10 in x 15 in3.51.7 to 20 20-in Supersonic Tunnel20 in dia1.4 - 5.00.5 - 20 NASA Glenn Research Center Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) 10 x 10 - ft Closed 10 x 10 Open 10 x 102 - 3.5 2 - 3.50.12 - 3.4 2.1 - 2.7 8 x 6 - ft 8 x 60.4 - 2.03.6 - 4.8 1 x 1 - ft 1 x 11.6 - 5.01.5 - 36 U. S. Department of Defense Arnold Engineering Development Center Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Propulsion Wind Tunnel Facility 16 S16 x 161.5 - 4.750.1 - 2.6 U. S. Aerospace Industry The Boeing Company Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Polysonic 4 x 40.20 - 5.84 - 50 Lockheed Martin Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) HSWT 4 x 40.4 - 4.84 - 34 Aero Systems Engineering Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) 13 1/2-in 13 1/2 in dianominally 1.5, 2, 2.5, 3, and 4 Allied Aerospace Industries - MicroCraft Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Tri-Sonic 7 x 7 ft0.1 - 3.52 - 19 Veridian - Calspan Operations Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Calspan Ludwieg Tube 5 ft dia2, 3.5, 4.514 CUBRC Wind TunnelTest Section (ft)Speed Range (Mach No.)Reynolds No. (per ft) LENS II 8 ft dia3 - 8 International Wind Tunnels Belgium Von Karman Institute for Fluid Dynamics Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. Transonic/supersonic wind tunnel S-1 40 cm x 40 cm 0.4 to 1.05, 1.43 2.0 and 2.25 4 x 106 /m Supersonic wind tunnel S-4 8 cm x 10 cm Mach 3.5 France Onera Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x 106) S2Ma 1.75 x 1.93 1.5 -3.14 S3Ma 0.76 x 0.801.65 - 5.53.2 Germany DLR - GermanAerospace Center Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x107)/m VMK Vertical Test Section Nozzel exit dia 150, 230, and 310 mm0.4 - 0.9, 1.57 - 3.225 TMK Trisonic Wind Tunnel 60 x 60 cm0.5 - 5.70.7 to 7 DNW - German-Dutch Wind Tunnels Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x106) RWG Ludwieg-Tube Wind Tunnel two sections: 0.5 x 0.5 & 0.5 diaLeg A: 3, & 4 Leg B: 5, 6, & 6.83.25 (Leg A) 2.2 (Leg B) TWG Transonic Wind Tunnel 1 x 10.3 < M < 0.9 (Subsonic Test Section) (0.5) - 0.85 < M < 1.2, (Transonic Test Section) 1.33 < M < 2.21 (Supersonic Test Section) 1.8 India National Aerospace Laboratories Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x 106) 1.2m Trisonic Tunnel (H1) 1.2 x 1.20.20 - 4.0 0.6m Transonic Tunnel (H2) 0.6 x 0.60.20 - 1.2 Netherlands DNW - German-Dutch Wind Tunnels Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x 106) CSST- Continuous Supersonic Tunnel 0.27 x 0.27M = 0.3 - 44 SST 1.2 x 1.2M = 1.2 to M = 415 Russia Central Aerohydrodynamic Institute TsAGI Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per m x 106) T-33 0.8 dia3 - 570 T-106 2.48 dia0.15 - 1.135 T-108 1 x 10.2 - 1.711 - 20 T-109 2.25 x 2.250.4 - 460 TPD 4 dia0.3 - 460 SVS-1 0.09, 0.16, 0.22 roundup to 2.0 SVS-2 0.5 x 0.516, 0.56 round0.3 - 6.0110 T-112 0.6 x 0.60.6 - 1.815 T-113 0.6 x 0.61.8 - 6.043 T-114 0.6 x 0.60.3 - 420 T-115 0.15 x 0.200.2 - 1.2, 2, 3, 43.8 T-128 2.75 x 2.750.15 - 1.741 Institute of Theoretical and Applied Mechanics Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per m x 106) T-313 (BD) 0.6 x 0.61.8 - 6.060 T-325 (BD) 0.2 x 0.20.5 - 420 T-333 (BD) 0.3 dia2 -550 Sweden FOI - Swedish Defence Research Agency Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. T1500 4 x 1.5 x 1.50.20 to 1.25, with slotted walls or 0.20 to 0.80 and 1.3 to 2.0, with solid wallsUp to 80 million/m S4 (transonic): 0.92 x 0.90 (supersonic): 0.90 x 1.15 0.5 - 2.0 800,000 - 1,600,000 /m S5 (transonic): 0.46 x 0.48 (supersonic): 0.46 x 0.570.5 - 3.6400,000 - 800,000 /m United Kingdom - Great Britain Flow Science - Goldstein Research Labratory Wind TunnelTest Section (m)Speed Range (Mach No.)Reynolds No. 0.21m x 0.15m Transonic / Supersonic Wind Tunnel supersonic 0.21 m x 0.15 m rectangular cross section by 0.8 m long2.0 Aircraft Research Association Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per m) Supersonic Wind Tunnel (SWT) 0.69 x 0.761.4 - 3.020 x 106 DERA Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per meter) 3 x 4 high speed Supersonic Tunnel 3ft x 4ft2.5 - 5.0 Hypersonic Wind Tunnels National Aeronautics & Space Administration NASA Langley Research Center NASA Glenn Research Center United States Department of Defense Arnold Engineering Development Center U.S. Aerospace Industry Boeing Aero Systems Engineering Verdian - Calspan Operation Calspan - University of Buffalo Research Center (CUBRC) International Installations Belgium Von Karman Institute for Fluid Dynamics France Onera Germany DLR - German Aerospace Center DNW - German-Dutch Wind Tunnels Russia Central Aerohydrodynamic Institute TsAGI Institute of Theoretical and Applied Mechanics Sweden FOI - Swedish Defence Research Agency United Kingdom Flow Science - Goldstein Research Laboratory Imperial College Aircraft Research Association National Aeronautics & Space Administration NASA Langley Research Center Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) 15-in Mach 6 High Temperature Tunnel 15 in dia60.5 to 8.0 20-in Mach 6 tunnel 20 in dia60.5 - 9 20-in Mach 6 CF4 Tunnel 20 in dia60.5 to 0.7 31-in Mach 10 Tunnel 31 in dia100.2 - 2.2 Direct Connect Supersonic Combustion Test Facility (Mach 2.0 nozzle) 1.52 in x 3.46 in (Mach 2.7 nozzle) 1.50 in x 6.69 in4.0 to 7.51.8 to 31.0 Combustion-Heated Scramjet Test Facility 42 in x 30 in x 96 in 3.5 to 6.01 to 6.8 Arc-Heated Scramjet Test Facility 4 ft dia4.7 to 8.00.04 to 2.2 8-ft high Temperature Tunnel 8-ft dia4, 5, 70.3 - 5.09 NASA Glenn Research Center Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Hypersonic Tunnel Facility 42 in dia x 120 in5 - 70.97 at Mach 7 to 2.41 at Mach 5 U.S. Department of Defense Arnold Engineering Development Center Wind Tunnel Facility Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Aerodynamic and Propulsion Test Unit Von Karman Gas Dynamics Facility High Pressure ARCS Hypervelocity Tunnel No. 9 5 dia7, 8, 10, 14, 16.50.072 at Mach 14 to 55.7 at Mach 8 U. S. Aerospace Industry Aero Systems Engineering Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) High Area Ratio Nozzle Test Stand and Hypersonic Wind Tunnel 20 in dia7, 11, 14 Boeing Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) B30 HST 12-inch diameter contoured nozzle 30-inch contoured nozzle Mach = 5 - 8 Mach = 8 - 20 Veridian - Calspan Operations Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft) Calspan 48 in shock tube 48 in dia5 - 18104-4x107 Calspan 96 in shock tube 96 in dia7 - 19104-7x107 CUBRC Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft) LENS 8 ft dia5.5 - 15 LENS II 8 ft dia3 - 8 International Installations Belgium Von Karman Institute for Fluid Dynamics Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. Hypersonic wind tunnel H-3 12 cm diameterMach 6 3 x 106 to 30 x 106 /m Longshot free piston hypersonic wind tunnel a Mach 14 contoured nozzle of 0.43 m exit diameter and a 6 degree conical nozzle of 0.60 m exit diameter15 to 205 x 106 to 15 x 106 /m France Onera Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x 106) S4Ma dia = 0.68, or 1, or 16.4, 10, 121.7, 0.9, 0.35 F4 dia = 670mm, or 670mm, or 430mm, or 930mm8-17, 7-13, 6-11, 9-21 2, 3, 5 ,1 Germany DLR - German Aerospace Center Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x106)/m L2K Arc-heated Facility Nozzle exit dia 100, & 200 mm4 to 8up to 0.01 L3K Arc-heated Facility Nozzle exit dia 100, 200, 300, & 400 mm5 to 10up to 0.1 H2K Hypersonic Wind Tunnel 36 cm 60 cm4.8 5.3, 6.0, 7.0, 8.7, and 11.2.20 DNW - German-Dutch Wind Tunnels Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (x106) RWG Ludwieg-Tube Wind Tunnel two sections: 0.5 x 0.5 & 0.5 diaLeg A: 3, & 4 Leg B: 5, 6, & 6.83.25 (Leg A) 2.2 (Leg B) Russia Central Aerohydrodynamic Institute TsAGI Wind TunnelTest Section (m)Speed Range (Mach No.)Reynolds No. (per m x 106) T-116 1 x 11.8 - 1047 T-117 2.5 x 2.4 x 1.9 10 - 184 T-120 0.15 dia4 - 1067 T-121 0.2 x 0.2 m ( M up to 6.0 ) 0.2 m ( M from 6.0 to 9.0 )4 - 950 IT-2 Diameter: 0.44 m (contoured nozzle) 0.2, 0.53, 0.9 m (conical nozzle)16.3 - 17.9 w/contoured nozzels, 10 - 22 w/conical nozzels40 ST-1 5 - 105.3 VAT-3 112, 18 Contoured nozzles 20 Conical nozzles0.03 - 1.5 T-131 1.25 - 7 2, 2.5, 3, 3.5, 4 w/ supersonic test rig10 Institute of Theoretical and Applied Mechanics Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per m x 106) T-326 (BD) 0.2 dia5 - 144 T-327 (VC) 0.22 dia16 - 250.2 UT-302 (HS) 0.3 dia5 - 15100 Sweden FOI - Swedish Defence Research Agency Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per meter) HYP500 (open Jet) 500 mm nozzle diameter 4, 7 United Kingdom - Great Britain Flow Science - Goldstein Research Laboratory Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. Mark II Tube 200 mm x 50 mmmach numbers to 15 Mark III Tube 60 mm square sectionmach numbers to 15 Imperial College Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. Hypersonic Gun Tunnel 0.34 m dia940 x 106 Low Density Hypersonic Wind Tunnel 0.20 m dia25 Aircraft Research Association Wind Tunnel Test Section (m)Speed Range (Mach No.)Reynolds No. (per m) Hypersonic Wind Tunnels (HWT) 0.3 x 0.44 - 560 x 106 (at Mach 4) 40 x 106 (at Mach 5) Hypersonic Wind Tunnels (HWT) 0.3 dia6, 7, 870 x 106 (at Mach 6) 50 x 106 (at Mach 7) 30 x 106 (at Mach 8) Propulsion Test Facilities National Aeronautics & Space Administration NASA Glenn Research Center United States Department of Defense Arnold Engineering Development Center U.S. Aerospace Industry Boeing Aero Systems Engineering GASL Calspan - University of Buffalo Research Center (CUBRC) International Installations National Aeronautics & Space Administration NASA Glenn Research Center Wind Tunnel Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Hypersonic Tunnel Facility 42 in dia x 120 in5 - 70.97 at Mach 7 to 2.41 at Mach 5 U.S. Department of Defense Arnold Engineering Development Center Wind Tunnel Facility Test Section (ft)Speed Range (Mach No.)Reynolds No. (per ft x 106) Aerodynamic and Propulsion Test Unit Von Karman Gas Dynamics Facility High Pressure ARCS U. S. Aerospace Industry Aero Systems Engineering Wind Tunnel Test Section (ft)Speed Range (Mach No.) High Area Ratio Nozzle Test Stand and Hypersonic Wind Tunnel 20 in dia7, 11, 14 Boeing Wind Tunnel Test Section (ft)Speed Range (Mach No.) B30 HST 12-inch diameter contoured nozzle 30-inch contoured nozzle Mach = 5 - 8 Mach = 8 - 20 GASL FacilityDuct (ft)Speed Range (Mach No.) Leg I Duct A - 6.6 in x 30 in max Duct B - 9 in x 30 in max2 - 8 Leg II 8.5 in x 32 in max2 - 8 Facility Test Section Speed Range (Mach No.) Leg V - Free jet Flight Acceleration Simulation Testing 6 ft dia, 15 ft long test cabin2 - 8 Facility Max Model Size Speed Range (Mach No.) Leg IV - Free jet Max Frontal Area - 120 in2 Max Length - 8 ft2 - 8 Facility Pressure Flow RateTime Leg IV - Gas Turbine Component Development 1500 psia40 lb/sec20 min Facility Pressure Temperature Heat Flux Leg III-POET (Panel Oxidation & Erosion) 1200 psia4500 oR3500 BTU/ft2/sec CUBRC Wind Tunnel Test Section (ft)Speed Range (Mach No.) LENS 8 ft dia5.5 - 15 LENS II 8 ft dia3 - 8 International Installations Boundary Layer Test Facilities International Installations Australia CSIRO Land and Water, Canberra Laboratories Canada The University of Western Ontario Norway Norwegian University of Science and Technology, Trondheim U.S. Installations International Installations Australia CSIRO Land and Water, Canberra Laboratories Wind Tunnel Test Section Speed Range Prye Laboratory Wind Tunnel 1.8m x 0.9m x 16m Canada The University of Western Ontario Wind Tunnel Test Section Speed Range BLWT1 2.4m x 2.1m x 33m0 - 15 m/sec BLWT2 High Speed Test Section: 3.4m x 2.5m x 39m Low Speed Test Section: 5.0m x 4.0m x 52m 2 m deep Wave Tank located in Low Speed Test Section0-30 m/s (HSTS) 0-10 m/s (LSTS) Hydraulic Wave Paddle (0-2Hz) Norway Norwegian University of Science and Technology, Trondheim Wind Tunnel Test SectionSpeed Range Boundary Layer Tunnel 1 1.4m x 0.3m x 5.6m Boundary Layer Tunnel 2 0.7m x 0.7m x 4m Large Scale Offshore Tunnel 1.8m x 2.7m x 11m Water Tunnels Flow Visualization Tunnels Altitude Chambers (no links for above pages) What's New Wind Tunnels Added: Low Speed Wind Tunnels Transonic Wind Tunnels Supersonic Wind Tunnels Hypersonic Wind Tunnels Other Facilities Wind Tunnels Updated: Low Speed Wind Tunnels Transonic Wind Tunnels Supersonic Wind Tunnels Hypersonic Wind Tunnels New Web Links Added: Professional Organizations Related Aerospace Links NASA Links Technical Reports Sign-up Here for Our Monthly Newsletter If you have any suggestions concerning the newsletter, let us know ! Stay tuned and sign-up. Press Releases If you have some interesting news concerning your facility, let us know. You may want to search for topics by keyword. Sponsorship By sponsoring the The Wind Tunnel Connection, you can reach hundreds of aerospace professionals. Corporate Sponsorship The Wind Tunnel Connection is looking for corporate sponsorships for this web site. As a corporate sponsor you will receive a banner and a link placed at a highly visible location on home page of The Wind Tunnel Connection. This is the perfect way to promote your company and its products to the aerospace community. It will also generate a steady traffic of interested wind tunnel surfers to your web site. The price, just $tbd per year. Individual Sponsorship If you like what you've found here and you think it is a valuable resource, you can help us keep this site up and running by becoming an individual sponsor. As an individual sponsor, your contribution of just $xx per year will help us keep the Wind Tunnel Connection free for all to use. Current Sponsors This website is currently made possible through the sponsorship of: TriModels, Inc. Advanced Technologies, Incorporated. For further information contact: The Worthey Connection The Wind Tunnel Connection Related Aerospace Resources Besides our wind tunnel listings, we have included links to online technical documents from NASA, the US Department of Defense, and many others. We also publish a quarterly newsletter. Previous issues are posted on this website and are available for download. The Wind Tunnel Connection relies on its user community to help us improve. If you have any suggestions as to how we can improve this website please let us know. Contact Information Telephone Electronic mail Webmaster: webmaster@worthey.net Thanks for coming by and we hope you come back soon to see our progress. This site has had visits since 01 January 2001. Technical Papers, Notes, and Reference Books This section contains a listing of a variety of technical papers, reference books and notes on a wide range of aerospace related topics. Some of the more significant works concerning wind tunnel testing are listed below. If you have any suggestions or recommendations that can add to this knowledge base please let us know by filling out our suggestion form or by emailing us at webmaster@worthey.net . Albert L. Braslow and Eugene C. Knox, "Simplified method for determination of critical height of distributed roughness particles for boundary-layer transition at Mach numbers from 0 to 5", NACA TN 4363, Sep 1958, pp. 19. Ames Research Staff, Equations, tables, and charts for compressible flow, NACA Report 1135, 1953, pp. 69. Benjamin H. Beam, A wind-tunnel test technique for measuring the dynamic rotary stability derivatives at subsonic and supersonic speeds, NACA Report 1258, Jan 1956, pp. 14. Home Suggestions About Reports NASA Reports NACA Reports NAS Reports DTIC Reports DERA Reports DSTO Reports AGARD Reports J.Fluid Mech J.M.Fluid Mech Shock Waves Theory & CFD Books Other Papers Notes Other Aerospace Related Sites Sponsor Sites Tri-Models - A precision designer and fabricator of wind tunnel models. Advanced Technologies, Inc. - A leading supplier of quality aerospace research and development products National Aeronautics and Space Administration NASA Home Page NASA Ames Research Center Numerical Aerospace Simulation Systems Division NASA Langley Research Center NASA Glenn Research Center Department of Defense Defense Technical Information Center US Air Force Air Force Research Laboratory Wright Laboratories Research Site US Navy Naval Air Systems Command Naval Air Warfare Center - Aircraft Division Naval Air Warfare Center - Weapons Division International Organizations North Atlantic Treaty Organization Aircraft Research Association Ltd. National Institute for Aerospace Research, Romania Council for Scientific and Industrial Research, South Africa Defense Evaluation and Research Agency, DERA, United Kingdom Central Aerohydrodynamic Institute TsAGI, Russia Institute of Theoretical and Applied Mechanics Professional Organizations American Institute of Aeronautics and Astronautics AIAA Ground Testing Technical Committee Society of Automotive Engineers (SAE) American Society of Civil Engineers (ASCE) ASMENET: ASME International U.S. Naval Institute The Supersonic Wind Tunnel Association The Subsonic Aerodynamic Testing Association Other Related Sites Air & Space Smithsonian Magazine National Air & Space Museum Discover Magazine Dan Raymer's Aircraft Design Site CFD Online Cornwall University Library Math Book Collection UIUC Airfoil Database Edinburgh Engineering Virtual Library Embry-Riddle Aeronautical University Virtual Library Model Rocket Equations The Wind Tunnels at NASA Ames By John Allmen, Deputy Chief (Acting) and Business Manager The Wind Tunnel Connection The Wind Tunnel Connection is a new service intended to be a resource to professional aerospace engineers involved in analyzing and testing new aerospace concepts. The service was initiated when it was discovered that many informational resources on wind tunnels were either seriously out of date or limited in scope. •
Contact
© Copyright 2024 Network Solutions, LLC. All rights reserved. All registered trademarks herein are the property of their respective owners.