Instability and Transition in the Mach-6 Quiet Tunnel

Schneider, Steven P.; Rufer, Shann J.; Skoch, Craig; Swanson, Erick; Borg, Matthew P.

doi:10.2514/6.2004-2247

Cited by 4 publications

(6 citation statements)

References 9 publications

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“…Schneider et al [160] report additional measurements of the free convection in the contraction before the run, which creates spatial and temporal nonuniformities that convect into the nozzle after the run begins. Most of the fluctuations appeared to occur near the wall.…”

Section: Shakedown and Modifications For Quiet Flowmentioning

confidence: 99%

“…Most of the fluctuations appeared to occur near the wall. A small jet of air blowing through the normal fill line into the upstream end of the driver tube did not affect the 8 psia (55 kPa) stagnation pressure at which the nozzle flow dropped quiet ( [160], pp. 9-10).…”

Section: Shakedown and Modifications For Quiet Flowmentioning

confidence: 99%

“…9-10). Although it is known from prior experience in the JPL tunnel that leaks in the settling chamber can cause jets of air that precluded quiet flow, leak tests in the Purdue tunnel using both pressure-drop measurements and a helium sniffer did not detect any leaks that seemed likely to preclude quiet flow ( [160], pp. 10-12).…”

Section: Shakedown and Modifications For Quiet Flowmentioning

confidence: 99%

“…10-12). The first operations with the new boost compressor are also reported ( [160], pp. [12][13][14].…”

Section: Shakedown and Modifications For Quiet Flowmentioning

confidence: 99%

“…Small transverse jets introduced via holes in the diffuser wall were able to separate the nozzle-wall boundary layer far upstream ( [160], pp. [14][15][16].…”

Section: Shakedown and Modifications For Quiet Flowmentioning

confidence: 99%

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Development of Hypersonic Quiet Tunnels

Schneider

2008

Journal of Spacecraft and Rockets

216

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Since then, he has focused on high-speed boundary-layer transition, developing facilities and instrumentation for detailed measurements under quiet-flow conditions. A $1 million 9.5-in. Mach-6 quiet-flow Ludwieg tube was completed in 2001 and achieved high Reynolds number quiet flow in 2006. He was promoted to professor, School of Aeronautics and Astronautics, in 2004, and has written seven review articles on hypersonic transition. He is an Associate Fellow of AIAA.

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Section: Shakedown and Modifications For Quiet Flowmentioning

confidence: 99%

Section: Shakedown and Modifications For Quiet Flowmentioning

confidence: 99%

Section: Shakedown and Modifications For Quiet Flowmentioning

confidence: 99%

“…10-12). The first operations with the new boost compressor are also reported ( [160], pp. [12][13][14].…”

Section: Shakedown and Modifications For Quiet Flowmentioning

confidence: 99%

“…Small transverse jets introduced via holes in the diffuser wall were able to separate the nozzle-wall boundary layer far upstream ( [160], pp. [14][15][16].…”

Section: Shakedown and Modifications For Quiet Flowmentioning

confidence: 99%

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Development of Hypersonic Quiet Tunnels

Schneider

2008

Journal of Spacecraft and Rockets

216

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Disturbances from Shock/Boundary Layer Interactions Affecting Upstream Hypersonic Flow

Skoch

2005

35th AIAA Fluid Dynamics Conference and Exhibit

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AFOSRApproved for public release. Distribution unlimited.Ph.D. Thesis documenting performance of unique national research facility.Large disturbances and decreased Mach number in the core flow were sometimes found in the downstream end of the nozzle of the Boeing/AFOSR Mach-6 Ludwieg Tube at Purdue University. The cause of the disturbances has been identified using Kulite pressure transducer, hot wire, and hot film measurements. These disturbances were found to be separations caused by shock/boundary-layer interactions in the diffuser, often originating from shocks generated at the sting support. Some disturbances were found to propagate upstream about 100 boundary layer thicknesses. The large upstream effect is due to the laminar boundary layers being very susceptible to separation. Attempts to prevent the separations from propagating upstream included an improved sting mount, compression rings to thin the boundary layer, and trip rings to trip the boundary layer. These attempts were not successful. A diffuser section with an increased area is proposed to prevent the separations from propagating upstream. My friends/officemates were helpful for bouncing ideas off of and at times distracting me from my research. I would like to thank Shann Rufer, Ben Kuperman

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Hot-Wire Measurements of Instability Waves on a Blunt Cone at Mach-6

Rufer

Schneider

2005

35th AIAA Fluid Dynamics Conference and Exhibit

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Hot wire calibrations were completed in the supersonic jet facility at Purdue University. This jet consists of a Mach-4 nozzle and allows for a continuous run time. The hot wires were calibrated under conditions similar to those seen in the Mach-6 facility at Purdue University. These hot wires were then used in the Mach-6 tunnel to study the amplitude and growth of instability waves on 7-deg half-angle sharp and blunt cones.

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Instability and Transition in the Mach-6 Quiet Tunnel

Cited by 4 publications

References 9 publications

Development of Hypersonic Quiet Tunnels

Development of Hypersonic Quiet Tunnels

Disturbances from Shock/Boundary Layer Interactions Affecting Upstream Hypersonic Flow

Hot-Wire Measurements of Instability Waves on a Blunt Cone at Mach-6

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