Hypersonic shock wave/turbulent boundary layer interactions in the vicinity of an expansion corner

White, Michael E.; Ault, David A.

doi:10.2514/6.1995-6125

Cited by 5 publications

(1 citation statement)

References 2 publications

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“…These studies indicated that reduction in the size of the separation bubble could not be achieved until the downstream edge of the separated region is near the expansion corner. 3 Pressure distribution, wave patterns and the extent of separation region were influenced especially when the shock impingement point was upstream of expansion corner. 4 However, when separation and reattachment both occur either upstream or downstream of the expansion corner, different shock strength induced interaction provided similar results.…”

Section: Figure 1 Typical Shock-wave Boundary Layer Interaction Nearmentioning

confidence: 99%

Experimental investigation of a Mach 4 shock-wave turbulent boundary layer interaction near an expansion corner

SathiaNarayanan

Verma

2015

53rd AIAA Aerospace Sciences Meeting

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Experimental investigation has been carried out to study the interaction between incident shock-wave and turbulent boundary layer near an expansion corner at a free stream Mach number of 3.9. The wedge angle (α), expansion angle (β) and the distance of inviscid impingement location (X) from the expansion corner were varied. Fin induced vortex dominated side wall flow was found to affect the complex interaction and make the interaction three dimensional which otherwise would be two dimensional. The line of separation is found to be independent of expansion corner angle even for the impingement downstream of expansion corner. With increase in wedge angle, the line of separation moves upstream. Peak pressure reduces with downstream impingement location and increase in expansion corner angle. Pressure far downstream of the interaction region is found to be nearly same irrespective of the configurations.

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Section: Figure 1 Typical Shock-wave Boundary Layer Interaction Nearmentioning

confidence: 99%

Experimental investigation of a Mach 4 shock-wave turbulent boundary layer interaction near an expansion corner

SathiaNarayanan

Verma

2015

53rd AIAA Aerospace Sciences Meeting

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Effect of expansion waves on cowl shock wave and boundary layer interaction in hypersonic inlet

Wu,

Wang,

Shi

et al. 2024

Propulsion and Power Research

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Investigation on Turbulent Expansion-Corner Flow With Shock Impingement

Chung

2000

Journal of Fluids Engineering

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Experiments are performed to study the interaction of an impinging shock wave and an expansion fan in a Mach 1.280 flow. The expansion fan neutralizes the pressure rise induced by the impinging shock wave. The mean surface static pressure shows a linear combination of the effect of both perturbations. Surface pressure fluctuations, which are associated with the characteristics of the perturbed boundary layer, indicate a transitional behavior. This is related to a nonlinear phenomenon arising the simultaneous action of the impinging shock wave and the expansion fan. The level of downstream pressure fluctuation depends on the overall inviscid interaction strength.

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Hypersonic shock wave/turbulent boundary layer interactions in the vicinity of an expansion corner

Cited by 5 publications

References 2 publications

Experimental investigation of a Mach 4 shock-wave turbulent boundary layer interaction near an expansion corner

Experimental investigation of a Mach 4 shock-wave turbulent boundary layer interaction near an expansion corner

Effect of expansion waves on cowl shock wave and boundary layer interaction in hypersonic inlet

Investigation on Turbulent Expansion-Corner Flow With Shock Impingement

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