Comparison of Experimentally Measured and Computed Second-Mode Disturbances in Hypersonic Boundary-Layers

Alba, Christopher R.; Casper, Katya M.; Beresh, Steven J.; Schneider, Steven P.

doi:10.2514/6.2010-897

Cited by 41 publications

(23 citation statements)

References 11 publications

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“…Although a few experiments have shown the dominance of the second-mode waves in the production of hypersonic turbulence and their disappearance in turbulent boundary layers [58], the detailed evolution of the second mode, especially its fast decay, has not been observed before. Schlieren or shadowgraph techniques can be used to observe the second mode [13], but the fine flow structures in the boundary layer cannot be fully resolved.…”

Section: Piv Resultsmentioning

confidence: 97%

Transition in Hypersonic Boundary Layers: Role of Dilatational Waves

et al. 2016

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Transition and turbulence production in a hypersonic boundary layer is investigated in the Mach 6 wind tunnel at Peking University, using Rayleigh-scattering visualization, fast-response pressure measurements, and particle image velocimetry. Detailed analysis of the experimental observations is provided. It is found that, although the second mode is primarily an acoustic wave, it causes the formation of high-frequency vortical waves. Moreover, the second mode interacts strongly with low-frequency waves, which leads to immediate transition to turbulence.freestream velocity, m∕s u = velocity vector, m∕s u = x component of the velocity, m∕s v = y component of the velocity, m∕s w = z component of the velocity, m∕s x = streamwise coordinate along the cone's surface, mm y = coordinate normal to the cone's surface, mm z = transverse coordinate normal to the x-y plane, mm= viscous normal stress, Pa ρ = density, kg∕m 3 τ f = flow time scale, s τ p = particle relaxation time, s Φ = viscous dissipation function per unit volume, kg∕m · s 3 ω = vorticity, 1∕s

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Section: Piv Resultsmentioning

confidence: 97%

Transition in Hypersonic Boundary Layers: Role of Dilatational Waves

et al. 2016

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“…The simulation setup follows the experimental study by Schneider and co-workers (Casper et al, 2009;Alba et al, 2010) in the Boeing/AFOSR Mach 6 Quiet Tunnel at Purdue University. They are currently conducting measurements of surface pressure fluctuations on a 7 degree sharp circular cone.…”

Section: Simulation Setupmentioning

confidence: 99%

Numerical Investigation of Laminar-Turbulent Transition in a Cone Boundary Layer at Mach 6

Sivasubramanian

2011

41st AIAA Fluid Dynamics Conference and Exhibit

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“…It is uncertain how pressure is transmitted to the sensing element through this epoxy, so the active sensing area is unknown. It has been stated earlier that the sensing element size was 0.039 × 0.063 in, [19][20][21][22][23] but further communication with PCB revealed that to be an error.…”

Section: B Model and Instrumentationmentioning

confidence: 92%

Pressure Fluctuation Measurements in the NASA Langley 20-Inch Mach 6 Wind Tunnel

Rufer

Berridge

2012

42nd AIAA Fluid Dynamics Conference and Exhibit

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Experiments have been carried out in the NASA Langley Research Center 20-Inch Mach 6Wind Tunnel to measure the freestream pressure fluctuations, or tunnel noise, using a pitot rake. These experiments are part of an on-going effort to characterize the freestream disturbances of the Langley hypersonic wind tunnels along with other facilities around the country. Once the freestream disturbances have been characterized, a better understanding of the effect of these disturbances on boundary layer instability and transition measurements can be gained. The current experiments use a multi-probe pitot rake instrumented with both Kulite and PCB pressure transducers. Data were obtained over a range of Reynolds numbers and test section axial and radial positions. In general, noise levels were consistent spatially across the test section and ranged from 1% at the highest Reynolds numbers tested to approximately 1.6% at the lowest Reynolds number tested.

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Comparison of Experimentally Measured and Computed Second-Mode Disturbances in Hypersonic Boundary-Layers

Cited by 41 publications

References 11 publications

Transition in Hypersonic Boundary Layers: Role of Dilatational Waves

Transition in Hypersonic Boundary Layers: Role of Dilatational Waves

Numerical Investigation of Laminar-Turbulent Transition in a Cone Boundary Layer at Mach 6

Pressure Fluctuation Measurements in the NASA Langley 20-Inch Mach 6 Wind Tunnel

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