Sensitivity analysis for the control of oblique shock wave/laminar boundary layer interactions at Mach 5.92

Nathaniel Hildebrand, Anubhav Dwivedi, Joseph W. Nichols, Graham V. Candler, Mihailo R. Jovanović

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

Abstract

At a transitional Reynolds number, we examine the instability of an oblique shock wave impinging on a hypersonic laminar boundary layer. Using global stability analysis we identify the critical oblique shock angle at which the 2D laminar flow first becomes unstable to 3D perturbations. The non-dimensional spanwise wavenumber selected at this bifurcation is β = 0.25. Long streamwise streaks that originate in the shear layer on top of the recirculation bubble are present in the unstable stationary global mode. We compute the adjoint eigenmodes to understand how upstream fluctuations affect the direct global modes of the system, and we see that the least stable stationary global mode is receptive to forcing inside the boundary layer and along the oblique shock wave. The wavemaker, which is defined as the sensitivity of an eigenvalue to base flow modification, is then computed. For every case, the wavemaker resides in the recirculation bubble, but it shifts towards the reattachment point as the incident shock angle increases. A calculation of the Görtler number about several 2D base flows revealed that a centrifugal instability cannot be the sole reason for bifurcation. There must be a feedback connection between Görtler vortices and the stationary behavior inside the recirculation bubble.

Original languageEnglish (US)
Title of host publication47th AIAA Fluid Dynamics Conference, 2017
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105005
StatePublished - Jan 1 2017
Event47th AIAA Fluid Dynamics Conference, 2017 - Denver, United States
Duration: Jun 5 2017Jun 9 2017

Publication series

Name47th AIAA Fluid Dynamics Conference, 2017

Other

Other47th AIAA Fluid Dynamics Conference, 2017
CountryUnited States
CityDenver
Period6/5/176/9/17

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  • Cite this

    Hildebrand, N., Dwivedi, A., Nichols, J. W., Candler, G. V., & Jovanović, M. R. (2017). Sensitivity analysis for the control of oblique shock wave/laminar boundary layer interactions at Mach 5.92. In 47th AIAA Fluid Dynamics Conference, 2017 (47th AIAA Fluid Dynamics Conference, 2017). American Institute of Aeronautics and Astronautics Inc, AIAA.