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

doi:10.2514/6.2016-3647

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 proceeding › Conference contribution

14 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 language	English (US)
Title of host publication	46th AIAA Fluid Dynamics Conference
Publisher	American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)	9781624104367
DOIs	https://doi.org/10.2514/6.2016-3647
State	Published - 2016
Event	46th AIAA Fluid Dynamics Conference, 2016 - Washington, United States Duration: Jun 13 2016 → Jun 17 2016

Publication series

Name	46th AIAA Fluid Dynamics Conference

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Other	46th AIAA Fluid Dynamics Conference, 2016
Country/Territory	United States
City	Washington
Period	6/13/16 → 6/17/16

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Publisher Copyright:
© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

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10.2514/6.2016-3647

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Interaction of an oblique shock with a transitional mach 5.92 boundary layer. / Shrestha, Prakash; Dwivedi, Anubhav; Hildebrand, Nathaniel et al.
46th AIAA Fluid Dynamics Conference. American Institute of Aeronautics and Astronautics Inc, AIAA, 2016. (46th AIAA Fluid Dynamics Conference).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Shrestha, P, Dwivedi, A, Hildebrand, N, Nichols, JW, 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, 46th AIAA Fluid Dynamics Conference, 2016, Washington, United States, 6/13/16. https://doi.org/10.2514/6.2016-3647

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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.",

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AU - Shrestha, Prakash

AU - Dwivedi, Anubhav

AU - Hildebrand, Nathaniel

AU - Nichols, Joseph W.

AU - Jovanovic, Mihailo

AU - Candler, Graham

PY - 2016

Y1 - 2016

N2 - 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.

AB - 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.

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ER -

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

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