Accession Number : AD0743260
Title : Quantitative Laser Schlieren Measurements in an Expanding Hypersonic Laminar Boundary Layer,
Corporate Author : TORONTO UNIV (ONTARIO) INST FOR AEROSPACE STUDIES
Personal Author(s) : Koziak,W. W.
Report Date : OCT 1971
Pagination or Media Count : 79
Abstract : The objective of the present work consists of two main parts. The first is the development of a quantitative space and time resolved schlieren systems. The second is the application of this technique to measure flow properties in the region of interaction of a hypersonic laminar boundary layer with a corner expansion wave and to compare these measurements with up-to-date theoretical results. A subject of currently renewed interest, the development of winged atmospheric entry vehicles having extensive cross range capabilities emphasizes the need to understand thoroughly hypersonic flow interaction phenomena such as the one investigated in the present thesis.
Descriptors : (*FLOWMETERS, HYPERSONIC FLOW), (*ATMOSPHERE ENTRY, HYPERSONIC FLOW), (*LAMINAR BOUNDARY LAYER, SCHLIEREN PHOTOGRAPHY), HYPERSONIC WIND TUNNELS, REENTRY VEHICLES, SHOCK WAVES, FLOW SEPARATION, TEST EQUIPMENT, CANADA, THESES
Subject Categories : Aerodynamics
Test Facilities, Equipment and Methods
Guided Missile Reentry Vehicles
Distribution Statement : APPROVED FOR PUBLIC RELEASE