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 18	1.55 - 2.5	1.0 to 6.0

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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 x7	1.5 to 2.9 2.3 to 4.6	0.5 to 6 0.5 to 11
Supersonic Low Disturbance Tunnel	6 in x 10 in x 15 in	3.5	1.7 to 20
20-in Supersonic Tunnel	20 in dia	1.4 - 5.0	0.5 - 20

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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 10	2 - 3.5 2 - 3.5	0.12 - 3.4 2.1 - 2.7
_{8 x 6 - ft}	8 x 6	0.4 - 2.0	3.6 - 4.8
1 x 1 - ft	1 x 1	1.6 - 5.0	1.5 - 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 S	16 x 16	1.5 - 4.75	0.1 - 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 4	0.20 - 5.8	4 - 50

Lockheed Martin

Wind Tunnel	Test Section (ft)	Speed Range (Mach No.)	Reynolds No. (per ft x 10⁶)
HSWT	4 x 4	0.4 - 4.8	4 - 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 dia	nominally 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 ft	0.1 - 3.5	2 - 19

Veridian - Calspan Operations

Wind Tunnel	Test Section (ft)	Speed Range (Mach No.)	Reynolds No. (per ft x 10⁶)
Calspan Ludwieg Tube	5 ft dia	2, 3.5, 4.5	14

CUBRC

Wind Tunnel	Test Section (ft)	Speed Range (Mach No.)	Reynolds No. (per ft)
LENS II	8 ft dia	3 - 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

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France

Onera

Wind Tunnel	Test Section (m)	Speed Range (Mach No.)	Reynolds No. (x 10⁶)
S2Ma	1.75 x 1.93	1.5 -3.1	4
S3Ma	0.76 x 0.80	1.65 - 5.5	3.2

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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 mm	0.4 - 0.9, 1.57 - 3.2	25
TMK Trisonic Wind Tunnel	60 x 60 cm	0.5 - 5.7	0.7 to 7

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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 dia	Leg A: 3, & 4 Leg B: 5, 6, & 6.8	3.25 (Leg A) 2.2 (Leg B)
TWG Transonic Wind Tunnel	1 x 1	0.3 < 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

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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 1.2	0.20 - 4.0
0.6m Transonic Tunnel (H2)	0.6 x 0.6	0.20 - 1.2

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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 0.27	M = 0.3 - 4	4
SST	1.2 x 1.2	M = 1.2 to M = 4	15

Russia

Central Aerohydrodynamic Institute TsAGI

Wind Tunnel	Test Section (m)	Speed Range (Mach No.)	Reynolds No. (per m x 10⁶)
T-33	0.8 dia	3 - 5	70
T-106	2.48 dia	0.15 - 1.1	35
T-108	1 x 1	0.2 - 1.7	11 - 20
T-109	2.25 x 2.25	0.4 - 4	60
TPD	4 dia	0.3 - 4	60
SVS-1	0.09, 0.16, 0.22 round	up to 2.0
SVS-2	0.5 x 0.516, 0.56 round	0.3 - 6.0	110
T-112	0.6 x 0.6	0.6 - 1.8	15
T-113	0.6 x 0.6	1.8 - 6.0	43
T-114	0.6 x 0.6	0.3 - 4	20
T-115	0.15 x 0.20	0.2 - 1.2, 2, 3, 4	3.8
T-128	2.75 x 2.75	0.15 - 1.7	41

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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 0.6	1.8 - 6.0	60
T-325 (BD)	0.2 x 0.2	0.5 - 4	20
T-333 (BD)	0.3 dia	2 -5	50

Sweden

FOI - Swedish Defence Research Agency

Wind Tunnel	Test Section (m)	Speed Range (Mach No.)	Reynolds No.
T1500	4 x 1.5 x 1.5	0.20 to 1.25, with slotted walls or 0.20 to 0.80 and 1.3 to 2.0, with solid walls	Up 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 0.57	0.5 - 3.6	400,000 - 800,000 /m

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United Kingdom - Great Britain

Flow Science - Goldstein Research Labratory

Wind Tunnel	Test 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 long	2.0

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Aircraft Research Association

Wind Tunnel	Test Section (m)	Speed Range (Mach No.)	Reynolds No. (per m)
Supersonic Wind Tunnel (SWT)	0.69 x 0.76	1.4 - 3.0	20 x 10⁶

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DERA

Wind Tunnel	Test Section (m)	Speed Range (Mach No.)	Reynolds No. (per meter)
3 x 4 high speed Supersonic Tunnel	3ft x 4ft	2.5 - 5.0

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Last modified: January 04, 2001