Accession Number : ADA258861


Title :   An Experimental Study of the Driving Mechanism and Control of the Unsteady Shock Induced Turbulent Separation in a Mach 5 Compression Corner Flow.


Descriptive Note : Doctoral thesis,


Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH


Personal Author(s) : McClure, William B


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a258861.pdf


Report Date : Jan 1992


Pagination or Media Count : 278


Abstract : This experimental study has examined the unsteady flowfield associated with the shock-induced separation of a turbulent boundary layer. The interaction was generated by a 28 deg unswept compression corner in a Mach 5 airstream. Perturbations were made to the interaction to better understand the mechanism responsible for the separation shock dynamics, as well as to demonstrate a method of controlling the shock motion. High frequency wall pressure measurements were used to track the time-dependent position of the separation shock. Conventional and fluctuating pitot pressure measurements were used to quantify the spatial mean and time-dependent extent of the baseline and altered interactions. Modification of the baseline interaction focused on two regions of the flowfield. Riblets and a boundary layer manipulator were separately introduced upstream of the interaction to alter the near-wall and outer region of the incoming boundary layer, respectively. Suction was applied through a slot in the face of the compression corner to alter the interaction downstream of the separation line.


Descriptors :   *TURBULENT BOUNDARY LAYER , COMPRESSIBLE FLOW , SEPARATION , MACH NUMBER , UNSTEADY FLOW


Subject Categories : Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE