Abstract
References
Information
The turbine-based combined cycle (TBCC) scramjet operates at a wide range of speeds, from subsonic to hypersonic. However, the effective inlet area is reduced due to factors such as adverse pressure gradient, boundary layer separation, and shockwave-boundary layer interaction. The effective inlet area decreases, leading to a decrease in suction and compression performance. As a result, a turbine engine may experience a stall or inlet unstart. This study performed a 3-dimensional computational analysis for each mode of the dual-path scramjet according to Mach number, altitude, and bleed flow control. The effective inlet area decreased due to an increase in altitude and a decrease in Mach number. The choking at the inlet was effectively suppressed because bleed flow control delays the flow separation.
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- Publisher :Korean Society for Computational Fluids Engineering
- Publisher(Ko) :한국전산유체공학회
- Journal Title :Journal of Computational Fluids Engineering
- Journal Title(Ko) :한국전산유체공학회지
- Volume : 28
- No :4
- Pages :7-15
Journal of Computational Fluids Engineering
