The Worthey Connection

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 22

0.20 - 1.50

0.3 - 9.6

  Return

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 15.5

0.2 - 1.25

1. to 4.

0.3M Transonic Cryogenic Tunnel

8 x 24 in

0.2 - 0.9

1 to 100

National Transonic Facility

8.2 x 8.2

0.1 - 1.2

4 to 146

Transonic Dynamics Tunnel (TDT)

16 x 16

0.1 - 1.2

0.03 to 3 (Air)
0.2 to 10 (R-134a)

  Return

NASA Marshall Space Flight Center

Wind Tunnel

Test Section (ft)

Speed Range
(Mach No.)

Reynolds No.
(per ft x 106)

High Re

32 in dia

0.30 - 3.50

7 - 200

  Return

 

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

  Return

 

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 12

0 - 1.15

0 - 4

Polysonic

4 x 4

0.20 - 5.8

4 - 50

Return

Aero Systems Engineering

Wind Tunnel

Test Section (ft)

Speed Range
(Mach No.)

Reynolds No.
(per ft x 106)

22-in

22 x 22 in

0 - 1.15

 

66-in

66 x 66 in

0 - 1.0

0 - 4.5

Return

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

Return

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

Return

Veridian - Calspan Operations

Wind Tunnel

Test Section (ft)

Speed Range
(Mach No.)

Reynolds No.
(per ft x 106)

Calspan

8 x 8 ft

0 - 1.35

0 - 12.5

  Return

 

International Wind Tunnels

 

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 m

0.3 – 1.2, continuously variable. 1.4 with replaceable nozzle

 

Return

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

Return

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 1.5m

0.1 to 0.75 subsonic
0.7 to 1.4 transonic
1.1 to 4.25 supersonic

 

Return

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 dia

0.05 - 1.0

7.9

S2Ma

1.75 x 1.77

0.1 - 1.3

5.4

S3Ma

0.56 x 0.78

0.1 - 1.3

3.5

Return

 

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 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

Return

DNW - German-Dutch Wind Tunnels

Wind Tunnel

Test Section (m)

Speed Range
(Mach No.)

Reynolds No.
(x106)

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

KRG - Cryogenic Ludwieg-Tube

cross section of 0.4 x 0.35² and a length of 2 m

0.30 < M < 0.95

78

Return

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

 

Return
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

HST

rectangular cross section 
2.00 x 1.60 or 1.80

M = 0 to 1.35

9

Return

 

Russia

Central Aerohydrodynamic Institute TsAGI

Wind Tunnel

Test Section (m)

Speed Range
(Mach No.)

Reynolds No.
(per m x 106)

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-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

Return

 

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 0.2

0.5 - 4

20

Return

 

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

Return

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 long

Mach 0.3 to Mach 0.9

 

Return

 

Aircraft Research Association

Wind Tunnel

Test Section (m)

Speed Range
(Mach No.)

Reynolds No.
(per m)

Transonic Wind Tunnel (TWT)

2.74 x 2.44

0.2 - 1.4

 

Two Dimensional Tunnel (2DT)

203 mm x 475 mm

0.3 - 0.87

 

Small Transonic Wind Tunnel (Z4T)

0.23 x 0.20

0.3 - 1.3

15 x 106

Return

DERA

Wind Tunnel

Test Section (m)

Speed Range
(Mach No.)

Reynolds No.
(per meter)

8 x 8 Pressurized High Speed

8ft x 8ft

 

 

Return