Optimal spatial growth of streaks in oblique shock/boundary layer interaction

Anubhav Dwivedi; Joseph W. Nichols; Mihailo Jovanovic; Graham V. Candler

doi:10.2514/6.2017-4163

Optimal spatial growth of streaks in oblique shock/boundary layer interaction

Anubhav Dwivedi, Joseph W. Nichols, Mihailo Jovanovic, Graham V. Candler

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

15 Scopus citations

Abstract

Direct numerical simulation (DNS) of oblique shock interacting with an incoming laminar boundary layer on an adiabatic at plate at Mach 5:92 is considered. Various shock angles are considered to simulate interactions at various strengths. Above a critical shock angle, the flow around the separation bubble becomes three dimensional and transition to turbulence ensues. Previous studies^{5, 11} point to the existence of three-dimensional streak like structures just before transition occurs. In order to investigate the origin and the linear amplification of steady streamwise structures after the reattachment, we use an adjoint looping algorithm suitable for investigating spatial optimal growth. We modify this approach to account for the effect of curvature of streamlines due to the presence of the separation bubble. We further comment on the role of the non-modal spatial growth in transition due to such an interaction. With this analysis we observe that the boundary layer downstream of reattachment can support significant growth. Furthermore, spanwise wavenumber of the optimal perturbation at the reattachment location matches quite well with the energetical spanwise scale observed in DNS for a range of shock angles.

Original language	English (US)
Title of host publication	8th AIAA Theoretical Fluid Mechanics Conference, 2017
Publisher	American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)	9781624104978
DOIs	https://doi.org/10.2514/6.2017-4163
State	Published - 2017
Event	8th AIAA Theoretical Fluid Mechanics Conference, 2017 - Denver, United States Duration: Jun 5 2017 → Jun 9 2017

Publication series

Name	8th AIAA Theoretical Fluid Mechanics Conference, 2017

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Other	8th AIAA Theoretical Fluid Mechanics Conference, 2017
Country/Territory	United States
City	Denver
Period	6/5/17 → 6/9/17

Bibliographical note

Funding Information:
This work was sponsored by Air Force Office of Scientific Research under grant number FA9550-12-1-0064 and the Office of Naval Research under grant number N00014-15-1-2522. The views and conclusions contained herein are those of the authors and should not be interpreted as necessarily representing the offcial policies or endorsements, either expressed or implied, of the funding agencies or the U.S. Government.

Publisher Copyright:
© 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

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Optimal spatial growth of streaks in oblique shock/boundary layer interaction. / Dwivedi, Anubhav; Nichols, Joseph W.; Jovanovic, Mihailo et al.
8th AIAA Theoretical Fluid Mechanics Conference, 2017. American Institute of Aeronautics and Astronautics Inc, AIAA, 2017. (8th AIAA Theoretical Fluid Mechanics Conference, 2017).

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

Dwivedi, A, Nichols, JW, Jovanovic, M & Candler, GV 2017, Optimal spatial growth of streaks in oblique shock/boundary layer interaction. in 8th AIAA Theoretical Fluid Mechanics Conference, 2017. 8th AIAA Theoretical Fluid Mechanics Conference, 2017, American Institute of Aeronautics and Astronautics Inc, AIAA, 8th AIAA Theoretical Fluid Mechanics Conference, 2017, Denver, United States, 6/5/17. https://doi.org/10.2514/6.2017-4163

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abstract = "Direct numerical simulation (DNS) of oblique shock interacting with an incoming laminar boundary layer on an adiabatic at plate at Mach 5:92 is considered. Various shock angles are considered to simulate interactions at various strengths. Above a critical shock angle, the flow around the separation bubble becomes three dimensional and transition to turbulence ensues. Previous studies5, 11 point to the existence of three-dimensional streak like structures just before transition occurs. In order to investigate the origin and the linear amplification of steady streamwise structures after the reattachment, we use an adjoint looping algorithm suitable for investigating spatial optimal growth. We modify this approach to account for the effect of curvature of streamlines due to the presence of the separation bubble. We further comment on the role of the non-modal spatial growth in transition due to such an interaction. With this analysis we observe that the boundary layer downstream of reattachment can support significant growth. Furthermore, spanwise wavenumber of the optimal perturbation at the reattachment location matches quite well with the energetical spanwise scale observed in DNS for a range of shock angles.",

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N2 - Direct numerical simulation (DNS) of oblique shock interacting with an incoming laminar boundary layer on an adiabatic at plate at Mach 5:92 is considered. Various shock angles are considered to simulate interactions at various strengths. Above a critical shock angle, the flow around the separation bubble becomes three dimensional and transition to turbulence ensues. Previous studies5, 11 point to the existence of three-dimensional streak like structures just before transition occurs. In order to investigate the origin and the linear amplification of steady streamwise structures after the reattachment, we use an adjoint looping algorithm suitable for investigating spatial optimal growth. We modify this approach to account for the effect of curvature of streamlines due to the presence of the separation bubble. We further comment on the role of the non-modal spatial growth in transition due to such an interaction. With this analysis we observe that the boundary layer downstream of reattachment can support significant growth. Furthermore, spanwise wavenumber of the optimal perturbation at the reattachment location matches quite well with the energetical spanwise scale observed in DNS for a range of shock angles.

AB - Direct numerical simulation (DNS) of oblique shock interacting with an incoming laminar boundary layer on an adiabatic at plate at Mach 5:92 is considered. Various shock angles are considered to simulate interactions at various strengths. Above a critical shock angle, the flow around the separation bubble becomes three dimensional and transition to turbulence ensues. Previous studies5, 11 point to the existence of three-dimensional streak like structures just before transition occurs. In order to investigate the origin and the linear amplification of steady streamwise structures after the reattachment, we use an adjoint looping algorithm suitable for investigating spatial optimal growth. We modify this approach to account for the effect of curvature of streamlines due to the presence of the separation bubble. We further comment on the role of the non-modal spatial growth in transition due to such an interaction. With this analysis we observe that the boundary layer downstream of reattachment can support significant growth. Furthermore, spanwise wavenumber of the optimal perturbation at the reattachment location matches quite well with the energetical spanwise scale observed in DNS for a range of shock angles.

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Optimal spatial growth of streaks in oblique shock/boundary layer interaction

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