INFLUENCE OF MACH NUMBER, NON-ADIABATIC WALLS AND NONLINEAR INTERACTIONS IN RESOLVENT ANALYSIS OF COMPRESSIBLE TURBULENT BOUNDARY LAYERS
Abstract
We propose a continuation of the study of resolvent analysis for compressible turbulent boundary layers, which has recently revealed formal similarity of the most amplified disturbances between the incompressible and compressible cases. The latter studies were restricted to adiabatic walls and Mach numbers up to 4, as well as the emerging importance of acoustic modes moving sonically relative to the local flow. Here we will increase the range of Mach numbers to the high Reynolds number regime, and extend our studies to include two-dimension, developing mean fields, nonadiabatic walls, and the implications for nonlinear forcing (excitation) in the compressible resolvent formulation. The goal is to provide a rigorous, non-empirical framework for the modeling of compressible wall turbulence in the absence of thermochemistry. We propose that this will contribute to Air Force needs for a framework for studying the development, structure, and ultimately control of compressible wall turbulence.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Aug 12, 2021
- Source ID
- FA95502010173
Entities
People
- Beverley McKeon
Organizations
- Air Force Office of Scientific Research
- California Institute of Technology
- United States Air Force