Temperature Measurements in a Hypersonic Boundary Layer Using Planar Laser-Induced Fluorescence
Author:
Affiliation:
1. Australian National University, Canberra, Australian Capital Territory 0200, Australia
2. Imperial College of Science, Technology, and Medicine, London, England SW7 2BY, United Kingdom
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/2.1172
Reference10 articles.
1. The interaction of a shock wave with a laminar boundary layer at a compression corner in high-enthalpy flows including real gas effects
2. Laser Diagnostics for Temperature and Species in Unsteady Combustion
3. A study of the free-piston shock tunnel.
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