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A Compilation of Hypersonic Facilities
•
University of Queensland
•
T4-Free Piston Driven Shock Tunnel
•
Compression tube: 229 mm ID x 26 m long
•
Piston mass: 92 kg
•
Shock tube: 76 mm ID x 10 m long
•
Contoured Nozzles:
•
Mach 4
•
Mach 6
•
Mach 7
•
Mach 8
•
Mach 10
•
Nozzle supply enthalpy range: 2.5 - 15 MJ/kg
•
Nozzle supply pressure range: 10 - 90 MPa
•
Drummond Tube
•
Shock tube: 3 m long x 62 mm diameter
•
Nozzles:
•
Conical Mach 4
•
Conical Mach 7
•
Contoured Mach 7
•
Typical operating conditions with He driving Air:
•
Supply enthalpy = 2 MJ/kg
•
Supply pressure = 2.2 MPa
•
X2 Super Orbital Expansion Tube
•
Diameter: 85 mm
•
Mach 4.8 - 0.3 - Moderate Enthalpy - 27 MJ/kg
•
Mach 7.3 - 0.2 - High Enthalpy (Nitrogen) - 61 MJ/Kg
•
Pressure: 67-1890 kPa - 28.21 - Moderate Enthalpy
•
Pressure: 3.3-220 kPa - 66.66 - High Enthalpy
•
Temperature: 4900-8500 K - Moderate Enthalpy
•
Temperature: 4800-11500 K - High Enthalpy
•
Piston Driven
•
X3 Expansion Tube
•
Diameter: 180 mm
•
Stagnation Enthalpies of about 100MJ/kg
•
Piston Driven
Free Piston Driven Shock Tube - Sandia National Laboratories
:
File
A Compilation of Hypersonic Facilities
•
University of Maryland
: High Speed Aerodynamics and Propulsion
Laboratory (
HAPL
)
•
HyperTERP
•
Built by group of Undergrads
•
Reflected Shock Tunnel with Mach-6 Jet Nozzle
•
Max.: 1500K and 2.5 MPa
•
Driver Section - 3 to 6 m (Extendable)
•
Driven Section - 6 m
•
Test Section: 48cm x 30cm x 30cm
•
High Temperature Ludweig Tube
•
Presently in Process - Halt due to COVID
•
Max. : 900K and 6 MPa
•
Two nozzles - Mach 6.2 and 8
•
Steady Test time - 100ms
•
AEDC Hypervelocity Wind Tunnel 9
•
Air Force's Tunnel 9
•
Upto Mach 14
•
Diameter: 1.524 m
•
Upto 15 sec test time
•
NASA Langley 20-Inch Mach 6 Tunnel
•
Collaboration b/w NASA and Air Force
•
Diameter: 0.5 m
•
Mach 6
•
Test Time over 15 mins
•
Stagnation Temperatures over 500K
•
Caltech: Hypersonics Group
•
T5 Reflected Shock Tunnel
A Compilation of Hypersonic Facilities
•
Free Piston Driven
•
Reservoir Enthalpy of upto 25 MJ/kg
•
Reservoir Pressure of upto 100 MPa
•
Reservoir Temp. of upto 10000K
•
Shock Propagation Speed Range from 2-5 km/s
•
Design Operation at Mach 5.2
•
Test Time : 1ms
•
Caltech Ludwieg Tube
•
Test Time : 50ms
•
Driven by a Pneumatic Cylinder
•
Mach 2.3 and Mach 4 (Starting Problems with the Mach 4 Nozzle)
•
Hypervelocity Expansion Tube (HET)
•
Impulse Facility
•
Inner Diameter of the three sections - Driver, Driven and acceleration
sections: 152 mm
•
Upto Mach 7.1 have been verifi ed
A Compilation of Hypersonic Facilities
•
Purdue University
•
Boeing/AFOSR
Mach 6
Quiet
Tunnel
•
Funded by Air Force Offi ce of Scientifi c Research, t
he Ballistic Missile
Defense Organization and the Boeing Company.
•
9.5 inch exit Diameter
•
Test time 10sec/hr
•
$10/shot
•
Ludwieg Tube
•
One of a kind Facility
•
Designed to achieve Laminar Nozzle Wall Boundary Layers
•
Hypersonic Pulse Shock Tunnel
(HYPULSE)
•
Donated by Northrop Grumman Corp.
•
Mach 5 to Mach 40 !
•
To be constructed
•
Only second University in US
•
Mach 8 Quiet Wind Tunnel
•
Air Force Research Laboratory
Funded
•
To be Constructed
•
One of a kind facility
•
Oxford University
•
T6 Stalker Tunnel
•
Created in collaboration with University of Queensland
•
Multi Mode Tunnel - Reflected Shock Tunnel, Expansion Tunnel and
Shock Tube
•
Driven by T3 free piston driver
•
Driven Tubes Mac. Pressure : 100 MPa (cap at 75 MPa)
•
Mach 7 and 8 contoured nozzles for reflected shock tunnel mode.
•
Actuated traverse +/- 15 deg AoA. +/- 5 deg AoY
A Compilation of Hypersonic Facilities
•
High Density Tunnel (HDT)
•
Operates
either as a Ludwieg tunnel or a Light Piston Compression
Heating facility
•
Cold Hypersonic Flow - To study the unsteady effects
•
Test time upto 70 ms
•
6.5 m long, 152 mm diameter driver
•
17.4 m long, 152 mm diameter barrel
•
Mach 3,4,5,7 and 7 contoured Nozzles
•
Actuated traverse +/- 15 deg AoA. +/- 5 deg AoY
•
Low Density Tunnel (LDT)
•
For rarefi ed flow
•
Slip Regimes can be experienced
•
Can measure aerodynamic coeffi cients by using a magnetic suspension
balance
•
Knudsen numbers up to 0.3
•
Max p0 = 200 kPa
•
Max T0 = 600 K
•
Contoured Mach 6 nozzle, 30-60 mm core flow
•
Mach 5-10 conical nozzle with 20-50 mm core flow
•
Magnetic force balance
•
2 axis wake traverse
•
3 axis traverse for model re-orientation
•
Cranfi eld University
•
Gun Tunnel
•
Blow Down wind tunnel
•
Mach 8.2 and 12.3
A Compilation of Hypersonic Facilities
•
High Speed Digital Schlieren Imaging system + data acquisition &
sensors.
•
Diameter: 200 mm
•
Driver Pressure upto 13.8 MPa
•
T0 Max. - 1290K
•
P0 Max. - 10.8 MPa
•
T Max. - 90K
•
University of Manchester
•
Hypersonic Wind Tunnel
•
7.5 second run time
•
Maximum velocity 1.2 km/s
•
Total pressure up to 850 kPa
•
Total temperature range 300-950 K
•
Mach 4, 5 and 6 nozzles w/ 6” diameter outlet and models up to 210mm
long
.
•
Reynolds Number Range
•
Mach 4.0: 0.4 million/metre to 38 million/metre
•
Mach 5.0: 0.2 million/metre to 25 million/metre
•
Mach 6.0: 0.6 million/metre to 10 million/metre
•
Imperial College London
•
NWTF Hypersonic Wind Tunnel
•
Diameter: 0.6 m and 1 m Length
•
Upto Mach 9
•
Slender Models 800+ mm can be tested
