关键词: 超音速冲压喷气发动机;Busemann进气道+;流线跟踪;数值仿真

Abstract: Inviscid calculations were performed to study the performance of 2-D full Busemann inlet, 3-D square streamtraced inlet, truncated full inlet and truncated streamtraced inlet at various flight Mach numbers, and to study the performance of truncated streamtraced inlet at angles of attack and angles of sideslip, which were all designed for Mach 7 flight and have a same contraction ratio of 6. The influence of viscosity on the performance of full and truncated inlets was investigated preliminarily. The results show that the full Busemann inlet has very high inviscid total pressure recovery, streamline tracing technique is so perfect that the starting performance of streamtraced inlet is much better and its efficiency at the design point is as high as the full Busemann inlet. The truncated inlet is much shorter with low losses of performance. Truncated streamtraced inlet is sensitive to the flight at angles of attack or sideslip. Viscosity causes higher total pressure losses.

Key words: Supersonic combustion ramjet engine;Busemann inlet~+;Streamline traced;Numerical simulation