Interaction of an oblique shock with a transitional mach 5.92 boundary layer

Prakash Shrestha, Anubhav Dwivedi, Nathaniel Hildebrand, Joseph W. Nichols, Mihailo Jovanovic, Graham Candler

Research output: Chapter in Book/Report/Conference proceedingConference contribution

4 Scopus citations

Abstract

We investigate the unsteadiness generated by an oblique shock impinging on a laminar Mach 5.92 boundary layer. Previous investigations found that a M = 2.15 boundary layer undergoes a three-dimensional bifurcation to linear instability. Using the US3D hypersonic flow solver, we investigate whether this bifurcation remains three- dimensional in the case of an oblique shock impinging on a laminar hypersonic boundary layer with M = 5.92. We characterize the frequency and spanwise wavenumber selected by this bifurcation using direct numerical simulation (DNS), sparsity-promoting dynamic mode decomposition (SPDMD), and global stability analysis. DNS reveals that the hypersonic boundary remains laminar for an oblique shock angle of θ = 12°, but becomes unstable and transitions to turbulence once the shock angle increases to θ = 14°. In this case, spanwise Fourier velocity spectra and SPDMD of the DNS data show that the flow selects a particular spanwise wavenumber and frequency. We confirm this frequency and wavelength via global stability analysis about steady two-dimensional baseows obtained from DNS.

Original languageEnglish (US)
Title of host publication46th AIAA Fluid Dynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624104367
DOIs
StatePublished - 2016
Event46th AIAA Fluid Dynamics Conference, 2016 - Washington, United States
Duration: Jun 13 2016Jun 17 2016

Publication series

Name46th AIAA Fluid Dynamics Conference

Other

Other46th AIAA Fluid Dynamics Conference, 2016
CountryUnited States
CityWashington
Period6/13/166/17/16

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    Shrestha, P., Dwivedi, A., Hildebrand, N., Nichols, J. W., Jovanovic, M., & Candler, G. (2016). Interaction of an oblique shock with a transitional mach 5.92 boundary layer. In 46th AIAA Fluid Dynamics Conference (46th AIAA Fluid Dynamics Conference). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2016-3647