An Experimental Study of the Glancing Interaction between a Shock Wave and a Turbulent  Boundary Layer

dc.contributor.author	A. Stanbrook	en_US
dc.date.accessioned	2014-10-20T11:02:45Z
dc.date.available	2014-10-20T11:02:45Z
dc.date.issued	1961	en_US
dc.identifier.other	ARC/CP-555	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/568
dc.description.abstract	An experimental study has been made at Mach numbers from 1.6 to 2.0 of the interaction between the turbulent boundary layer on a side wall of a wind tunnel and the shock wave produced by a plate mounted on the wall. Under these conditions the shock wave/boundary layer interaction was three dimensional at least over the region investigated (up to 10 boundary layer thicknesses from the plate).	en_US
dc.relation.ispartofseries	Aeronautical Research Council Current Papers	en_US
dc.title	An Experimental Study of the Glancing Interaction between a Shock Wave and a Turbulent Boundary Layer	en_US