Shock-Induced Turbulence and Acoustic Loading on Aerospace Structures
Abstract
Shock-wave turbulent-boundary layer interaction (SWTBLI) is of particular interest to structural engineers of aerospace structures. Pulsating flows featuring unsteadiness caused by SWBLI can lead to structural damage and/or fatigue and must be taken into account in the design of supersonic and hypersonic aerostructures. Pozefsky et al. has estimated that the time to failure of a hypersonic (local) structure can be of the order of one minute or less, and the critical locations are always associated with flowfields dominated by SWBLI and shock/shock interactions. Advancing our understanding of the SWBLI unsteadiness and associated acoustic loading is also important for developing effective control strategies that will mitigate fluctuating load intensity, or altering its spectral content. The aim of this project is to apply HR and HO methods to supersonic/hypersonic turbulent SWBLI and supersonic/hypersonic boundary layers inducing acoustic loading on the structure, and investigate both the accuracy and efficiency of these methods in the framework of advanced CFD methods, such as implicit large eddy simulation (ILES) and hybrid ILES/Reynolds-Averaged-Navier-Stokes (RANS).
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Mar 23, 2016
- Source ID
- FA95501510501
Entities
People
- Dimitris Drikakis
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Strathclyde