Shakedown of the Purdue Mach-6 quiet-flow Ludwieg tube

Schneider, Steven P.; Rufer, Shann J.; Randall, Laura; Skoch, Craig

doi:10.2514/6.2001-457

Cited by 11 publications

(9 citation statements)

References 15 publications

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“…The roughness Reynolds number Re k (or ρ k u k k∕μ k ) was calculated using results from the Harris and Blanchard [36] finite difference boundary-layer code. The best estimate for the equilibrium temperature distribution on the interior of the nozzle was obtained from Skoch [37] and Schneider et al [38] using a finite element heat transfer simulation (see Sec. III).…”

Section: F Calculation Of Reynolds Numbersmentioning

confidence: 99%

“…The best estimate for the equilibrium temperature distribution on the interior of the nozzle was obtained by Skoch [37] and Schneider et al [38] using a finite element heat transfer (FEHT) simulation for heat transfer in the nozzle. In the simulation, Skoch [37] modeled the initial 0.88 m of the nozzle.…”

Section: Effect Of Temperature On Computed Boundary-layer Propertiesmentioning

confidence: 99%

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Hypersonic Boundary-Layer Instabilities due to Near-Critical Roughness

Wheaton

Schneider

2014

Journal of Spacecraft and Rockets

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Measurements of instability and transition were obtained in the wake of a cylindrical roughness within the laminar nozzle-wall boundary layer of the Purdue Mach-6 Quiet Tunnel. Using wall-mounted pressure transducers along the wake centerline, the root-mean-square pressure and power spectra were computed to find evidence of instabilities within the roughness wake. The roughness height was adjusted to explore the case of incipient transition on the nozzle wall. It appeared that small variations in the experimental parameters could have a large effect on transition for the near-critical case. Several dominant disturbance frequencies were identified for a selected set of conditions. These disturbances appear to be due to instabilities developing within the wake of the roughness. The streamwise evolution of these disturbances are reported, as well as the spanwise distribution at one streamwise location within the wake. The experimentally observed disturbances can be used as a test case to continue to develop methods for computing the stability of roughness wakes. Nomenclature D = cylindrical roughness diameter, mm k = cylindrical roughness height, mm p 0 = tunnel stagnation pressure, kPa p 0 = fluctuating component of pressure, kPa Re k = roughness Reynolds number, ρ k u k k∕μ k Re k;crit = critical roughness Reynolds number Re ∞ = unit freestream Reynolds number, 1∕m T driver = temperature from a thermocouple at the upstream end of the driver tube, K T nozzle = mean temperature recorded by the thermocouples on the nozzle, K T 0 = tunnel stagnation temperature, K t = time after the diaphragm burst, s x = streamwise distance downstream from the central axis of the roughness, mm z = spanwise arc length from the center of the roughness, mm δ = boundary-layer thickness, defined as the height where the local velocity is 99.5% of the freestream value Subscripts i = initial condition k = roughness height condition ∞ = freestream condition

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Section: F Calculation Of Reynolds Numbersmentioning

confidence: 99%

Section: Effect Of Temperature On Computed Boundary-layer Propertiesmentioning

confidence: 99%

Hypersonic Boundary-Layer Instabilities due to Near-Critical Roughness

Wheaton

Schneider

2014

Journal of Spacecraft and Rockets

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“…temp." shows a computation for the Purdue tunnel using a good approximation to the actual temperature distribution along the nozzle at a stagnation temperature of 780 R (433K) and a stagnation pressure of 150 psia (1034 kPa) [145]; the estimated quiet Reynolds number is much lower and approximately the same as that in the NASA Langley nozzle. A full-scale Mach-6 nozzle that is 33 ft (10 m) long with a 24in.…”

Section: Boeing/air Force Office Of Scientific Research Mach-6 Quiet mentioning

confidence: 99%

“…Schneider et al [145] describe the system for heating the contraction and computations of the temperature distribution along the first part of the nozzle. The temperature drops below 40 C by about 20 in.…”

Section: Design and Initial Fabricationmentioning

confidence: 99%

“…The electroformed throat was plated from a hard-nickel bath that improves polishability and reduces the risk of scratching. Unfortunately, the maximum temperature for the hard nickel was found to be only slightly higher than the stagnation temperature (typically 433K) due to an unexpected state change in this nickel near 470 K ( [145], pp. [12][13].…”

Section: Design and Initial Fabricationmentioning

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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