Easterwood Complex Wind Tunnel Facilities
Actively
Controlled Expansion Hypersonic Tunnel (ACE-HT)
The ACE Hypersonic Wind Tunnel
is a blow-down facility, with a continuously variable Mach number (M = 5 to 7).
The Mach number is varied by actively controlling the nozzle expansion ratio,
which can be achieved many times during a typical 2.0 minute run. The test
section dimension is 0.229 m x 0.356 m. This facility was designed and
constructed by the Bowersox Research Group.
Photographs of the ACE Hypersonic Tunnel
during installation in the TAMUNA Laboratory
NASA Langley Mach 6.0 Quiet Tunnel (M6QT)
The M6QT was built as part of
the Langley Hypersonic Facility Complex (currently known as the
Aerothermodynamic Laboratory Complex) to provide a low-disturbance environment
required for boundary-layer transition and instability testing. The wind tunnel
was relocated to Texas A&M University (TAMU) in 2005, where it is currently
being reassembled in the Easterwood TAMUNA Laboratory. This tunnel has a 0.184
m diameter test section. For more information see the Flight Research Lab M6QT
website, or for a complete description see Chen et al (AIAA Paper No. 91-1648, 1991)
and Blanchard et al (AIAA J., 35, No. 1, pp 23-28., 1997).
Schematic of the M6QT as installed in the TAMUNA Lab
and a photograph of the nozzle mandrill
Dynamics Stall Facility (DSF)
The DSF is an in-house designed
and constructed addition to the Oran Nicks
Low-Speed Wind Tunnel to allow for detailed measurements of the
leading-edge flow during dynamics stall at flow conditions (Mach number and
Reynolds Number) matching those for helicopter flight. This facility consists
or inserts to the Low-Speed tunnel that accelerate the flow to up to Mach 0.4
and provide the support structure dynamically pitching wings (NACA 0012 and
Sikorsky A09). Both wings have 0.457 m chord lengths and 2.14 m spans. A
hydraulic actuation system is used to oscillate the wings at up to 10 Hz.
Schematic of the tunnel inserts, hydraulic
system and wing in the tunnel (tunnel prop is in the background)
Supersonic Basic Research Tunnel (SBRT)
A small-scale, 7.62 cm x 7.62
cm, supersonic blow-down wind tunnel was designed and constructed by the
Bowersox Group. The purpose of the tunnel is to perform basic studies of
boundary layer and jet interaction flow phenomena. The available Mach numbers
are 2.2, 3.0 and 5.0. This facility can operate for approximately 30 minutes.
Photographs of the SBRT (M = 2.2
Configuration) and the Mach 5.0 Nozzle
Plasma Turbulence Research Tunnel
(PTRT)
The PTRT is a continuous flow
subsonic (Velocity = 70 m/s) facility designed and constructed by our group to study
the effects of molecular (vibrational) non-equilibrium on the decay rate of the
turbulence kinetic energy. A Capacitively-Coupled Radio Frequency (CCRF)
sustained plasma is used to introduce molecular non-equilibrium into the flow,
while the translation energy remains minimally affected near room temperature.
This facility is also being using to further develop a suite of advanced laser
diagnostics to study fundamental processes in this class of flow.
Photographs of the PTRT and the CCRF Plasma
Field
Impulse Facilities: High-Enthalpy Shock
Tube/Tunnel and the Double Barrel
Ludwig Tunnel
Two impulse facilities, a
high-enthalpy shock tunnel and a “double barrel” Ludwig tunnel,
were installed as part of an undergraduate research program supported by the
NSF (REU program). The shock tunnel facility provides true temperatures under
tailored operation for flight Mach numbers up to 10. A unique nozzle is under
development for this facility. This facility is used to study chemical kinetics
and hypersonic aerothermochemistry. The Ludwig tunnel and the shock tunnel are
also used for basic gasdynamic experiments and to further advance laser
diagnostics.
Photograph of the shock tube and Ludwig
tube, double diaphragm holder and a wave diagraph for Mach 8.7 operation of the
shock tunnel