Experimental investigations of test gas effects on the hypersonic flow field around large angle blunt cone in shock tunnel
Author:
Affiliation:
1. Tohoku Univ., Sendai, Japan
2. Indian Inst. of Science, Bangalore, India
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2001-305
Reference11 articles.
1. Forebody Convective Hypersonic Heat Transfer Measurements over Large-Angle Blunt Cones
2. Hypersonic convective heat transfer over 140-deg blunt cones in different gases
3. High-Enthalpy Aerothermodynamics of a Mars Entry Vehicle Part 1: Experimental Results
4. A theoretical model for the shock stand-off distance in frozen and equilibrium flows
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1. Heat Transfer Measurements over Large Angle Blunt Cones Entering Martian Atmosphere;Journal of Spacecraft and Rockets;2013-05
2. Expansion Tube Investigation of Shock Stand-Off Distances in High-Enthalpy CO2 Flow Over Blunt Bodies;48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition;2010-01-04
3. Visualization of shock waves around hypersonic spiked blunt cones using electric discharge;Journal of Visualization;2005-03
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