期刊
INTERNATIONAL JOURNAL OF HEAT AND FLUID FLOW
卷 85, 期 -, 页码 -出版社
ELSEVIER SCIENCE INC
DOI: 10.1016/j.ijheatfluidflow.2020.108677
关键词
Compressible flows; Turbulent boundary layers; Nonmodal stability analysis; Resolvent analysis; Coherent structures; Large scale motions
资金
- Air Force Office of Scientific Research [FA9550-16-1-0232]
This work applies resolvent analysis to compressible zero-pressure-gradient turbulent boundary layers with freestream Mach numbers between 2 and 4, focusing exclusively on large scale motions in the outer region of the boundary layer. We investigate the effects of Mach number on predicted flow structures, and in particular, look at how such effects may be attributed to changes in mean properties. By leveraging the similarity between the compressible and incompressible resolvent operators, we show that the shape of the streamwise velocity and temperature components of resolvent response modes in the compressible regime can be approximated by applying ideas from wavepacket pseudospectral theory to a simple scalar operator. This gives a means of predicting the shape of resolvent mode components for compressible flows without requiring the singular value decompositions of discretized operators. At a Mach number of 2, we find that accurate results are obtained from this approximation when using the compressible mean velocity profile. At Mach numbers of 3 and 4, the quantitative accuracy of these predictions is improved by also considering a local effective Reynolds number based on the local mean density and viscosity.
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