Supersonic combustion - A shock tunnel and vitiation-heated blowdown tunnel comparison
Author:
Affiliation:
1. Queensland, Univ., Brisbane, Australia
2. National Aerospace Lab., Kakuda, Japan
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1998-941
Reference14 articles.
1. Ignition and Combustion Performance of Scramjet Combustors with Fuel Injection Struts
2. Experiments on supersonic combustion ramjet propulsion in a shock tunnel
3. Low-thrust LO2/LH2 engine performance with a 300 - 1 nozzle
4. Edenfield, E.E."Design of a High Reynolds Number Mach Number 8 Contoured Nozzle for the Hypervelocity Wind Tunnel (F)",AEDC-TR-72-48 (1972).
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