TY - GEN
T1 - Development of stability analysis tools for high speed compressible flows
AU - Bhagwat, Rutvij R.
AU - Subbareddy, Pramod K.
N1 - Publisher Copyright:
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
Copyright:
Copyright 2018 Elsevier B.V., All rights reserved.
PY - 2018
Y1 - 2018
N2 - We present some recent work related to the development of stability analysis tools for high speed compressible flows. High speed flows are often dominated by shocks, and exhibit a host of other interacting flow features such as boundary layers and acoustic waves. Techniques such as global stability analysis and resolvent analysis are useful for the analysis of these flows. Some validation results for simple configurations such as a compressible mixing layer, compressible boundary layer, incompressible flow over a cylinder, and incompressible channel flow are presented. Results for a hypersonic flow over a wedge have been discussed along with potential for future work.
AB - We present some recent work related to the development of stability analysis tools for high speed compressible flows. High speed flows are often dominated by shocks, and exhibit a host of other interacting flow features such as boundary layers and acoustic waves. Techniques such as global stability analysis and resolvent analysis are useful for the analysis of these flows. Some validation results for simple configurations such as a compressible mixing layer, compressible boundary layer, incompressible flow over a cylinder, and incompressible channel flow are presented. Results for a hypersonic flow over a wedge have been discussed along with potential for future work.
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U2 - 10.2514/6.2018-3381
DO - 10.2514/6.2018-3381
M3 - Conference contribution
AN - SCOPUS:85051284134
SN - 9781624105531
T3 - 2018 Fluid Dynamics Conference
BT - 2018 Fluid Dynamics Conference
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 48th AIAA Fluid Dynamics Conference, 2018
Y2 - 25 June 2018 through 29 June 2018
ER -