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 | |
| 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 |
|---|
Other
| Other | 46th AIAA Fluid Dynamics Conference, 2016 |
|---|---|
| Country/Territory | United States |
| City | Washington |
| Period | 6/13/16 → 6/17/16 |
Bibliographical note
Publisher Copyright:© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.