Abstract
Despite over fifty years of research on shock wave boundary layer effects and interactions, many related technical issues continue to be controversial and debated. The present survey provides an overview of the present state of knowledge on such effects and interactions, including discussions of: (i) general features of shock wave interactions, (ii) test section configurations for investigation of shock wave boundary layer interactions, (iii) origins and sources of unsteadiness associated with the interaction region, (iv) interactions which included thermal transport and convective heat transfer, and (v) shock wave interaction control investigations. Of particular interest are origins and sources of low-frequency, large-scale shock wave unsteadiness, flow physics of shock wave boundary layer interactions, and overall structure of different types of interactions. Information is also provided in regard to shock wave investigations, where heat transfer and thermal transport were important. Also considered are investigations of shock wave interaction control strategies, which overall, indicate that no single shock wave control strategy is available, which may be successfully applied to different shock wave arrangements, over a wide range of Mach numbers. Overall, the survey highlights the need for additional understanding of fundamental transport mechanisms, as related to shock waves, which are applicable to turbomachinery, aerospace, and aeronautical academic disciplines.
Highlights
Introduction and backgroundShock waves are present in a variety of engineering application environments, such as transonic gas turbine blade tip gaps, transonic turbine blade passages, scramjet isolator ducts, supersonic aircraft engine intakes, adjacent to transonic and supersonic flight vehicle surfaces, and nearby surfaces of rockets, missiles, and reentry vehicles
These different application environments require consideration of the orientation, position, strength, and unsteadiness of the associated shock waves. The interactions between such shock waves and the boundary layers of these devices are of particular interest
Discussed third are the origins and sources of unsteadiness associated with the interaction region
Summary
Different diffuser configuration and flow parameters are related to shock wave interaction features, including frequencies of unsteadiness. Robinet and Casalis [15] numerically determined that the relationship between the diffuser length and shock wave oscillation frequency was caused by weak shock wave reflections at the diffuser exit This conclusion was verified by Handa et al [16] using experimental and numerical techniques, who attributed much shock wave motion to large pressure fluctuations, which appeared to originate at locations downstream of shock waves, where the flow was highly turbulent. Sajben and Kroutil [13], Edwards and Squire [17], Ott et al [18], Handa et al [16], and Bur et al [19] utilized experimental and numerical approaches to consider the effects of a variable-geometry second throat With these approaches, shock wave boundary layer interaction response to a controlled, oscillatory, back pressure was addressed. This was because the shock-induced separation was very sensitive to changes in the shock strength at a specific Mach number
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