Factors influencing flow steadiness in laminar boundary layer shock interactions

Tumuklu, Ozgur; Levin, Deborah A.; Gimelshein, S. F.; Austin, Joanna

doi:10.1063/1.4967555

Cited by 11 publications

(3 citation statements)

References 14 publications

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“…In Ref. 10, it was concluded that the relative magnitude of the specific heat ratio has a significant impact on the SWBLI (Shock Wave/Boundary Layer Interaction). Specifically, the flow of argon resulted in a separation bubble with 1.8 times the size of the one for nitrogen and, due to the endothermic effects of finite-rate chemistry, the size of this region was 1.5 times smaller for air than for nitrogen.…”

Section: Introductionmentioning

confidence: 99%

Characterization of nonequilibrium shock interaction in CO2-N2 flows over double-wedges with respect to Mach number and geometry

2023

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The characterization of the shock interaction mechanism originating from the high-Mach nonequilibrium flow over double-wedge geometries is key to the design of hypersonic vehicles. The impact of changes in the freestream Mach number and double-wedge geometry on the patterns of shock interaction is investigated by means of numerical simulation in the case of CO2-N2 flows. The extended laminar Navier–Stokes equations with a two-temperature model to account for translational-to-vibrational internal energy transfer are considered the physical model of this type of flow. Simulations show that reducing the freestream Mach number leads to an increase in the separation region, both in the compression corner and in the locations of shock impingement. The impact of the size of the separation region on the patterns of interaction is such that it causes variations in the type of shock interaction. From the point of view of the flow physics near the wedges, decreasing the freestream Mach number has an equivalent effect to increasing the angle of the second wedge and an opposite effect to increasing the freestream temperature on the pattern of interaction. Results show that decreasing the freestream Mach number leads to an overall reduction in pressure and heating loads along the surface of the wedges and smaller regions of thermal equilibrium behind the bow shock.

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Section: Introductionmentioning

confidence: 99%

Characterization of nonequilibrium shock interaction in CO2-N2 flows over double-wedges with respect to Mach number and geometry

2023

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“…Additionally, larger aft angles lead to a larger standoff distance of the bow shock, higher probability of shock impingement on the wall and overall increasing complexity of the interaction mechanism, potentially leading to instability of the shear layers or unsteady interaction patterns [5,8]. Efforts have also been made in the attempt to better understand the influence of the gas mixture and/or specific heat ratio on the physics of shock interactions [9,10]. Tumuklu et al compared the flow over a 30°-55°double-wedge for three different gas mixtures: air, nitrogen, and argon [9].…”

Section: Introductionmentioning

confidence: 99%

“…In Ref. [10], the role of the gas mixture was further investigated. It was concluded that the relative magnitude of the specific heat ratio has a significant impact on SBLI (Shock Boundary Layer Interaction).…”

Section: Introductionmentioning

confidence: 99%

Response of shock interaction patterns to different freestream conditions in carbon-dioxide flows over double-wedges

Garbacz

Morgado

Fossati

2022

AIAA AVIATION 2022 Forum

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The shock interaction originating from a hypersonic laminar flow over a double-wedge can lead to different flow patterns depending on geometrical parameters such as the lengths and angles of the each wedge, as well as flow parameters such as the mixture and freestream conditions. In this work, the effect of the freestream Mach number on the patterns of shock interaction is numerically investigated for a CO 2 -N 2 nonequilibrium flow over different double-wedge geometries. The numerical analysis is performed by solving the laminar Navier-Stokes equations within the framework of a two-temperature model to account for translational-vibrational internal energy transfer. Results show that the size of separated flow regions, both in the compression corner and locations of shock impingement, increase with decreasing Mach number. This revealed to have a significant impact on the patterns of interaction, since the size of a separation region dictates if additional shocks are generated, potentially leading to more complex mechanisms of interaction. It was concluded that decreasing the freestream Mach number has a similar impact as increasing the angle of the second wedge on the pattern of interaction. The parametric study also shows that decreasing the freestream Mach number leads to overall lower surface pressure and heating, as well as smaller regions of thermal equilibrium.

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Linear Instability of Shock-Dominated Laminar Hypersonic Separated Flows

Sawant

Tumuklu

Theofilis

et al. 2021

IUTAM Laminar-Turbulent Transition

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Factors influencing flow steadiness in laminar boundary layer shock interactions

Cited by 11 publications

References 14 publications

Characterization of nonequilibrium shock interaction in CO2-N2 flows over double-wedges with respect to Mach number and geometry

Characterization of nonequilibrium shock interaction in CO2-N2 flows over double-wedges with respect to Mach number and geometry

Response of shock interaction patterns to different freestream conditions in carbon-dioxide flows over double-wedges

Linear Instability of Shock-Dominated Laminar Hypersonic Separated Flows

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