Results 11 to 20 of about 116,720 (315)
Journal of Fluid Science and Technology, 2011 The interaction of a spatially transitional boundary layer flow at freestream Mach number M = 2.0 with an impinging oblique shock wave (β = 35.56) is studied by means of direct numerical simulation (DNS).
Yusuke TOKURA, Hiroshi MAEKWA
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Recent investigations of shock wave effects and interactions
Advances in Aerodynamics, 2020 Despite over fifty years of research on shock wave boundary layer effects and interactions, many related technical issues continue to be controversial and debated.
P. M. Ligrani +4 more
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Pseudo-shock waves and their interactions in high-speed intakes [PDF]
, 2016 In an air-breathing engine the flow deceleration from supersonic to subsonic conditions takes places inside the isolator through a gradual compression consisting of a series of shock waves.
Gnani, F., Kontis, K., Zare-Behtash, H.
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Journal of Engineering, 2023 The objective of this paper is to numerically study the shock wave/boundary layer interaction and boundary layer separation. The first stage of this research is the development of methodology, flow simulations, and data analysis. When comparing the plots,
Ana Maria Pereira Lara +1 more
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Transient Flow Evolution of a Hypersonic Inlet/Isolator with Incoming Windshear
Aerospace, 2023 In this paper, a novel flow perturbation model meant to investigate the effects of incoming wind shear on a hypersonic inlet/isolator is presented. This research focuses on the transient shock/boundary layer interaction and shock train flow evolution in ...
Simin Gao +5 more
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Experimental Study of the Unstart/Restart Process of a Two-Dimensional Supersonic Inlet Induced by Backpressure [PDF]
Journal of Applied Fluid Mechanics, 2022 Unstart/restart phenomena induced by backpressure in a general inlet with a freestream of M = 2.7 are investigated in an in-draft supersonic quiet wind tunnel.
Y. L. Zhao, Y. Y. Zhou, Y. X. Zhao
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Transition Effect on the Flow Dynamics in a Compressor Blade Passage
Shock and Vibration, 2021 An experimental investigation was carried out to study the effect of the boundary layer transition on the flow dynamics in the blade passage of a compressor cascade.
Ryszard Szwaba +2 more
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Zones of Influence and Shock Motion in a Shock Boundary Layer Interaction [PDF]
49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2011 This paper aims at describing the main features of a shock reflection on a turbulent boundary layer. The data used for this analysis are the results of large-eddy simulations of the interaction carried out with three different shock intensities: from incipient to fully separated cases. Computational results are validated vs experiments obtained for the
Agostini, Lionel +4 more
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Advances in Mechanical Engineering, 2019 At hypersonic speeds, the external wall temperatures of an aerospace vehicle vary significantly. As a result, there is a considerable heat transfer variation between the boundary layer and the wall of the hypersonic vehicle.
Amjad A Pasha, Khalid A Juhany
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Study of Parameters Affecting Separation Bubble Size in High Speed Flows using k-ω Turbulence Model [PDF]
Journal of Applied and Computational Mechanics, 2018 Shock waves generated at different parts of vehicle interact with the boundary layer over the surface at high Mach flows. The adverse pressure gradient across strong shock wave causes the flow to separate and peak loads are generated at separation and ...
Amjad Ali Pasha
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