不同抽吸孔布局的进气道数值模拟机理分析  

Mechanism Analysis of Inlet with Different Suction Slots Layout by Numerical Simulation

作　　者：刘波[1] LIU Bo(Shenghua Group Zhunguner Energy CO.,LTD,Inner Mongolia Zhungeer 017000,China)

机构地区：[1]神华准格尔能源有限责任公司,内蒙古准格尔017000

出　　处：《现代防御技术》2021年第2期43-48,共6页Modern Defence Technology

摘　　要：采用标准k-ωSST湍流模型数值计算方法,针对2种不同抽吸孔布局的超声速进气道数值进行了模拟机理分析。结果表明:在抽吸孔前缘引起的膨胀波与唇口反射激波相交,马赫数增加;模型-1在抽吸孔内形成循环涡流,马赫数增加到3.6,并在抽吸孔内多次反射,在抽吸孔出口的马赫数降低;而模型-2由于在受到剪切层的影响,在抽吸孔内形成循环涡流变成亚声速区域;在抽吸孔后缘形成强压缩波,与进气道反射激波多次相交,模型-2的进气道上壁面下游的压力整体趋势大于模型-1的壁面压力。Mechanism analysis of supersonic inlet with two suction slot layout using standard k-ωSST turbulence model with numerical calculation method.The results show that:Mach number increased due to interaction with reflected shock wave and expansion wave caused by the leading edge of the suction slot;A circulate eddy is formed in the suction slot and multiple reflected in model-1.The Mach number increases to 3.6.and then decreased in the;A subsonic region is formed in the suction slot of model-2 due to shear layer,and a strong compression wave is formed at the rear edge of the suction slot,which intersect with the reflected shock wave many times.Upper wall pressure of model-2 is larger than model-1 with the overall trend.

关 键 词：抽吸孔 反射激波 剪切层 湍流模型 机理分析 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程] TJ760.3[兵器科学与技术—武器系统与运用工程]