激波与转捩边界层干扰非定常特性数值分析
发布时间：2019-04-24 06:54
【摘要】：激波与边界层干扰的非定常问题是高速飞行器气动设计中基础研究内容之一.以往研究主要针对层流和湍流干扰,在分离激波低频振荡及其内在机理方面存在着上游机制和下游机制两类截然不同的理论解释.分析激波与转捩边界层干扰下非定常运动现象有助于进一步加深理解边界层状态以及分离泡结构对低频振荡特性的影响规律,为揭示其产生机理指出新的方向.采用直接数值模拟方法对来流马赫数2.9,24?压缩拐角内激波与转捩边界层干扰下激波的非定常运动特性进行了数值分析.通过在拐角上游平板特定的流向位置添加吹吸扰动激发流动转捩,使得进入拐角的边界层处于转捩初期阶段.在验证了计算程序可靠性的基础上,详细分析了转捩干扰下激波运动的间歇性和振荡特征,着重研究了分离泡展向三维结构对激波振荡特性的影响规律,最后还初步探索了转捩干扰下激波低频振荡产生的物理机制.研究结果表明:分离激波的非定常运动仍存在强间歇性和低频振荡特征,其时间尺度约为上游无干扰区内脉动信号特征尺度的10倍量级;分离泡展向三维结构不会对分离激波的低频振荡特征产生实质影响.依据瞬态脉动流场的低通滤波结果,转捩干扰下激波低频振荡的诱因来源于拐角干扰区下游,与流场中分离泡的收缩/膨胀运动存在一定的关联.
[Abstract]:The unsteady problem of shock wave and boundary layer interaction is one of the basic research contents in aerodynamic design of high-speed aircraft. Previous studies have focused on laminar and turbulent interferences, and there are two distinct theoretical explanations, upstream mechanism and downstream mechanism, on the low-frequency oscillation and its internal mechanism of shock separation. The analysis of unsteady motion phenomenon under the interaction of shock wave and transition boundary layer is helpful to further understand the influence of boundary layer state and separation bubble structure on the low-frequency oscillation characteristics, and to point out a new direction for revealing the mechanism of its generation. By using the direct numerical simulation method, the Mach number of the incoming flow is 2.9, 24? The unsteady motion characteristics of shock wave under the interaction of shock wave in compression angle and transition boundary layer are numerically analyzed. The boundary layer entering the corner is in the initial stage of transition by adding blow-suction disturbance to stimulate the flow transition at the specific direction of the plate upstream of the corner. On the basis of verifying the reliability of the calculation program, the intermittent and oscillatory characteristics of shock wave motion under transition disturbance are analyzed in detail, and the effects of the three-dimensional structure of the separated bubble on the shock oscillation characteristics are emphatically studied. Finally, the physical mechanism of low-frequency oscillation of shock wave caused by transition interference is also discussed. The results show that the unsteady motion of the separated shock still has the characteristics of strong intermission and low frequency oscillation, and its time scale is about 10 times that of the characteristic scale of the pulsating signal in the upstream non-interference region. The three-dimensional structure of the separated bubble will not have a substantial effect on the characteristics of the low-frequency oscillation of the separated shock wave. According to the low-pass filtering results of transient pulsating flow field, the inducement of low-frequency oscillation of shock wave under transition interference comes from the downstream of corner interference region, which is related to the contraction / expansion motion of separated bubbles in the flow field.
【作者单位】： 中国空气动力研究与发展中心计算空气动力所;中国科学院力学研究所高温气体动力学国家重点实验室;中国科学院大学工程科学学院;
【基金】：国家自然科学基金资助项目(91441103,11372330,11472278)
【分类号】：V211
[Abstract]:The unsteady problem of shock wave and boundary layer interaction is one of the basic research contents in aerodynamic design of high-speed aircraft. Previous studies have focused on laminar and turbulent interferences, and there are two distinct theoretical explanations, upstream mechanism and downstream mechanism, on the low-frequency oscillation and its internal mechanism of shock separation. The analysis of unsteady motion phenomenon under the interaction of shock wave and transition boundary layer is helpful to further understand the influence of boundary layer state and separation bubble structure on the low-frequency oscillation characteristics, and to point out a new direction for revealing the mechanism of its generation. By using the direct numerical simulation method, the Mach number of the incoming flow is 2.9, 24? The unsteady motion characteristics of shock wave under the interaction of shock wave in compression angle and transition boundary layer are numerically analyzed. The boundary layer entering the corner is in the initial stage of transition by adding blow-suction disturbance to stimulate the flow transition at the specific direction of the plate upstream of the corner. On the basis of verifying the reliability of the calculation program, the intermittent and oscillatory characteristics of shock wave motion under transition disturbance are analyzed in detail, and the effects of the three-dimensional structure of the separated bubble on the shock oscillation characteristics are emphatically studied. Finally, the physical mechanism of low-frequency oscillation of shock wave caused by transition interference is also discussed. The results show that the unsteady motion of the separated shock still has the characteristics of strong intermission and low frequency oscillation, and its time scale is about 10 times that of the characteristic scale of the pulsating signal in the upstream non-interference region. The three-dimensional structure of the separated bubble will not have a substantial effect on the characteristics of the low-frequency oscillation of the separated shock wave. According to the low-pass filtering results of transient pulsating flow field, the inducement of low-frequency oscillation of shock wave under transition interference comes from the downstream of corner interference region, which is related to the contraction / expansion motion of separated bubbles in the flow field.
【作者单位】： 中国空气动力研究与发展中心计算空气动力所;中国科学院力学研究所高温气体动力学国家重点实验室;中国科学院大学工程科学学院;
【基金】：国家自然科学基金资助项目(91441103,11372330,11472278)
【分类号】：V211
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