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Thermal and inertial parameters of the flow field of a scramjet engine
Jigar Sura,Satheesh Kumar,Viren Menezes 대한기계학회 2015 JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY Vol.29 No.11
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 thereonfrom 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 ofpeak heating that may require additional thermal protection during the operation; the regions being the beginning of the constant areaduct and the nozzle. The pressure measurements and the pertinent analysis indicated an optimum compression at intake through shockwaves with a viable flow separation in the combustion chamber. The experimental data indicated an optimum design of the engine for apossible fuelled operation in future.