抽吸位置对固冲发动机进气道性能的影响

For a solid rocket ramjet with design Mach number of 3， two-dimensional numerical simulation was used to study the effects of suction holes at different locations on the unstart Mach number，anti-back pressure capability and total pressure recovery coefficient of an inlet with adjustable primary gas flow，i.e. a large range of back pressure changes. By setting suction holes in the inner compression section，the unstart Mach number of the inlet was reduced from 2.7 to 2.4，and the anti-back pressure capability was increased by 12.28%; The unstart Mach number of the inlet decreased from 2.7 to 2.6 due to the suction of the outer compression section，and the anti-back pressure capability was not improved; however，the anti-back pressure capability of throat suction inlet was increased by 11.24%，and the unstart Mach number did not change. The internal compression section and throat section suction can improve the total pressure recovery under certain working conditions，especially the total pressure recovery coefficient under over rated working conditions. Finally，a scheme to improve the performance of the inlet under Mach number of 3—5 was proposed，and the total pressure recovery under Mach number of 4—5 was increased by about 5% on average.