Record Details


Field	Value

Title	Thermal and inertial parameters of the flow field of a scramjet engine

Creator	SURA, J KUMAR, S MENEZES, V

Subject	Heat flux Hypersonic Pressure Scramjet

Description	Heat flux and pressure were measured on the internal walls of a scramjet engine at a hypersonic Mach number of 8 in a shock tunnel. Temperature-time history was recorded on model walls using fast-response thermocouples and the wall heat flux was deduced thereon from the temperature records. Pressure was measured at the same locations as that of heat flux using high-frequency pressure transducers. The surface measurements were used to analyze the internal flow field of the engine. The heat flux measurements revealed the regions of peak heating that may require additional thermal protection during the operation; the regions being the beginning of the constant area duct and the nozzle. The pressure measurements and the pertinent analysis indicated an optimum compression at intake through shock waves with a viable flow separation in the combustion chamber. The experimental data indicated an optimum design of the engine for a possible fuelled operation in future.

Publisher	KOREAN SOC MECHANICAL ENGINEERS

Date	2016-01-14T12:38:55Z 2016-01-14T12:38:55Z 2015

Type	Article

Identifier	JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY, 29(11)4943-4950 1738-494X 1976-3824 http://dx.doi.org/10.1007/s12206-015-1042-9 http://dspace.library.iitb.ac.in/jspui/handle/100/17518

Language	en

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