Demonstration Of Supersonic Combustion In A Combustion Driven Shock-Tunnel

Demonstration Of Supersonic Combustion In A Combustion Driven Shock-Tunnel

For flights beyond Mach 6 ramjets are inefficient engines due to huge total pressure loss in the normal shock systems, combustion conditions that lose a large fraction of the available chemical energy due to dissociation and high structural loads. However if the flow remains supersonic inside the co...

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Bibliographic Details
Main Author: Joarder, Ratan
Other Authors: Jagadeesh, G
Language:en_US
Published: 2011
Subjects:
Supersonic Combustion
Shock Tunnel
Air Injection
Hypersonic Flow
Combustion - Numerical Simulations
Combustion-Driven Shock Tunnel
Hypersonic Shock Tunnel HST2
Supersonic Flow
Jet Injection
Hypersonic Cross-flow
Heat Engineering
Online Access:http://hdl.handle.net/2005/1005

Internet

http://hdl.handle.net/2005/1005

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