Numerical Investigation of Asymmetric Mach 2.5 Turbulent Shock Wave Boundary Layer Interaction

Numerical Investigation of Asymmetric Mach 2.5 Turbulent Shock Wave Boundary Layer Interaction

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Supersonic shock wave boundary layer interactions are common to inlet flows of supersonic and hypersonic vehicles. This paper reports on wall-resolved implicit large-eddy simulations of a canonical Mach 2.5 turbulent shock wave boundary layer interaction experiment at the NASA Glenn Research Center....

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Bibliographic Details
Main Authors: John-Paul Mosele, Andreas Gross, John Slater
Format: Article
Language:English
Published: MDPI AG 2023-04-01
Series:Aerospace
Subjects:
supersonic flow
asymmetric flow
shock wave boundary layer interaction
turbulent separation
unsteady flow
large-eddy simulation
Online Access:https://www.mdpi.com/2226-4310/10/5/417
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