Quantitative Laser Schlieren Measurements in an Expanding Hypersonic Laminar Boundary Layer,
TORONTO UNIV (ONTARIO) INST FOR AEROSPACE STUDIES
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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.
- Test Facilities, Equipment and Methods
- Guided Missile Reentry Vehicles
- Fluid Mechanics