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.
Quantitative Laser Schlieren Measurements in an Expanding Hypersonic Laminar Boundary Layer
1971
79 pages
Report
No indication
English
Fluid Mechanics , Aerodynamics , Laboratory & Test Facility Design & Operation , Missile Warheads & Fuses , Flowmeters , Atmosphere entry , Laminar boundary layer , Hypersonic flow , Schlieren photography , Hypersonic wind tunnels , Reentry vehicles , Shock waves , Flow separation , Test equipment , Canada , Theses
Pulsed-Laser Schlieren Visualization of Hypersonic Boundary-Layer Instability Waves
British Library Conference Proceedings | 1994
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