Influence of Mach Number, Non-Adiabatic Walls and Nonlinear Interactions in Resolvent Analysis of Compressible Turbulent Boundary Layers
Abstract
The challenges associated with observing high-speed boundary layers are well known. In the turbulent regime, there is rarely sufficient observation time to fully characterize statistics or structures. Models for understanding and for large eddy simulation typically rely on a range of assumptions and empirical but tested assumptions. In this work, we seek to develop resolvent analysis for developing turbulent boundary layers under conditions approaching realistic for applications of interest, in particular with regards to Mach number and wall cooling. The subsequent results are used to describe commonalities and differences between the flows of interest and incompressible turbulent boundary layers, with a view to understanding when and how knowledge from the better-studied incompressible case may be applied to compressible turbulence, as well as characterizing the physical forcing exciting truly compressible responses in the flow. We exploit the latter for a proof of concept demonstration of modeling the disturbance field radiated into the freestream from a turbulent boundary layer, an important concern for stability experiments on models mounted in the freestream.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 04, 2023
- Accession Number
- AD1231058
Entities
People
- Beverley McKeon
Organizations
- California Institute of Technology