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原文传递 Investigation of "6X" Scramjet Inlet Configurations.

题名：	Investigation of "6X" Scramjet Inlet Configurations.
作者：	Alter, S. J.
关键词：	Aerodynamic Configurations; Boundary Layers; Engine Inlets; Hypersonic Inlets; Hypersonic Speed; Supersonic Combustion; Supersonic Combustion Ramjet Engines; Technology Utilization; Vortices
摘要：	This work represents an initial attempt to determine what, if any, issues arise from scaling demonstration supersonic combustion scramjets to a flight scale making the engine a viable candidate for both military weapon and civilian access to space applications. The original vehicle sizes tested and flown to date, were designed to prove a concept. With the proven designs, use of the technology for applications as weapon systems or space flight are only possible at six to ten times the original scale. To determine effects of scaling, computations were performed with hypersonic inlets designed to operate a nominal Mach 4 and Mach 5 conditions that are possible within the eight foot high temperature tunnel at NASA Langley Research Center. The total pressure recovery for these inlets is about 70%, while maintaining self start conditions, and providing operable inflow to combustors. Based on this study, the primary scaling effect detected is the strength of a vortex created along the cowl edge causing adverse boundary layer growth in the inlet.
报告类型：	科技报告