钝锥高超音速绕流脉冲扰动研究  

Study on the effect of pulse perturbation in hypersonic flow over a blunt cone

作　　者：王振清[1] 唐小军 孟祥男[1] 吕红庆 

机构地区：[1]哈尔滨工程大学航天与建筑工程学院,黑龙江哈尔滨150001

出　　处：《哈尔滨工程大学学报》2013年第3期298-305,共8页Journal of Harbin Engineering University

基　　金：教育部博士点基金资助项目(20112304110015);中央高校基本科研业务费资助项目(HEUCF100204;HEUCF110204)

摘　　要：为了探究来流脉冲扰动波对高超音速流动的干扰,采用7阶迎风WENO格式对无粘通量项离散和6阶中心差分格式对粘性项离散,并使用3阶总变差减少龙格-库塔法进行时间推进求解N-S方程.基于6马赫绕钝锥自由来流,在稳定流场来流外边界加入一个脉冲扰动波,直接数值模拟了脉冲扰动的演变发展过程,并基于ABAQUS有限元软件模拟了钝锥体的瞬态压力响应,分析了对气动热力学特性及钝锥力学特性的影响.结果显示,数值方法精确捕捉到了脉冲扰动的演变发展,在脉冲波作用下,弓形激波出现变形,来流扰动波参数被放大数倍甚至数十倍,近壁面区域产生了涡;流场气动热力学特性和结构压力响应显著地受到脉冲波扰动影响,钝锥头部区域表面的热力学特性变化趋势显著地异于非头部区域,且前者变化较后者显著,后者沿驻点线大致呈线性增长趋势.The research study explored the interaction between hypersonic flow and pulse disturbance wave in free-stream,as a result of the seventh-order upwind weighted essentially non-oscillatory（WENO） scheme and the sixth-order center difference scheme used to discretize inviscid flux vectors and viscous flux vectors,respectively.The third-order total variation diminishing（TVD） Runge-Kutta scheme was also employed for time integration to solve Navier-Stokes equations.Based on 6 mach free-stream over a blunt cone,an ultra-short pulse disturbance was introduced at the upstream end of the computational domain to do direct numerical simulation（DNS） of the evolution and development process of the strong pulse wave;based on finite element software ABAQUS to simulate the transient process of pressure response.The effects of pulse wave on aerothermodynamics properties and structural mechanical behavior of blunt cone were investigated.The results show that the development of the pulse disturbance was captured accurately by using numerical methods.The bow shock was bent obviously under the action of pulse wave;the amplitude of pulse wave was enlarged several and even dozens of times relative to that of initial disturbance in free-stream,and eddy was generated near the wall surface region while being subjected to perturbation wave.In addition,the aerothermodynamics properties and structural mechanical properties were influenced obviously;the aerothermodynamics parameters on the wall of nose were significantly different from that on the wall of non-nose;the former changed more sharply than the latter;and the latter has a linear growth along the stagnation line.

关 键 词：脉冲扰动 高超音速流动 钝锥 高阶精度 直接数值模拟 

分 类 号：O369[理学—流体力学]