脉冲波作用下的高超音速非定常流动模拟及影响研究  

Numerical Simulation and Impact Studies of Hypersonic Unsteady Flow Under the Action of Pulse Disturbance Wave

作　　者：孟祥男[1] 王振清[1] 唐小军 吕红庆 

机构地区：[1]哈尔滨工程大学航天与建筑工程学院,哈尔滨150001

出　　处：《应用数学和力学》2013年第2期127-138,共12页Applied Mathematics and Mechanics

基　　金：国家自然科学基金资助项目(11272096);高等学校博士学科点专项科研基金资助项目(20112304110015);中央高校基本科研业务费专项资金资助项目(HEUCF100204)

摘　　要：采用高阶精度有限差分方法模拟了快声波脉冲扰动作用下的高超音速非定常流场,分析了脉冲波与高超音速流场的相互干扰,并应用Fourier频谱分析研究扰动波在边界层的发展.结果表明:来流脉冲扰动波与激波及边界层强烈相互作用,弓形激波明显向内弯曲,激波后扰动波被显著放大;来流扰动波与弓形激波干扰形成的边界层外的扰动波和近壁面内形成的边界层扰动波存在明显分界.钝锥头部参数扰动幅值要远大于其他位置参数扰动幅值.在边界层内的发展阶段,一些扰动模态持续增长,一些扰动模态被过滤掉,不再增长,甚至衰减,而也有一些扰动模态先衰减再增长.总的来说,在钝锥头部低频扰动模态为主导模态,随着扰动从流场上游向下游发展,总扰动模态中的低频模态成份和高频模态成份所占的比例开始转变,高频模态成分显著地增大.Direct numerical simulation of pulse disturbance in hypersonic flow over a blunt cone by using high-order accuracy finite difference method was performed.The interaction between fast acoustic wave and hypersonic flow field was studied;the evolution and development process of disturbance wave in the boundary layer was analyzed by Fourier frequency spectral analysis（FFSA）.Results show that the disturbance into the flow field interacted with the shock wave and boundary layer,which makes bow shock bent obviously and disturbance enlarged,with obvious demarcations between the disturbance near the wall and in the outer boundary layer.The perturbation amplitudes on the nose are much larger than on the other locations.At the stage of the development of disturbance in the boundary layer,some perturbation modes continue to grow,some are filtered and seldom grow,even decay,and also some decay firstly and then grow.In general,the low frequency perturbation modes are dominated within a nose radius,with the disturbance development from upstream to downstream,the high frequency components increase quickly and low frequency components almost are restrained to grow.

关 键 词：高超音速 边界层 脉冲扰动 快声波 Fourier频谱分析 

分 类 号：O351[理学—流体力学]