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 |