【作者】 蒋旭旭；

【导师】 王革；

【作者基本信息】 哈尔滨工程大学 ， 航空宇航推进理论与工程， 2006， 硕士

【摘要】 激波与边界层相互作用在高速飞行中无所不在，通常发生在飞机、导弹和火箭的内、外流场，激波诱导的边界层分离常带来如流道雍塞等诸多棘手问题，是当今热点研究课题之一。本文针对二维平板／楔结构，数值模拟了由尖楔产生的激波冲击平板诱导平板边界层产生分离的现象。通过分别改变来流马赫数M_∞及楔角θ以改变入射激波强度，计算并比较了不同强度入射激波与平板边界层相互干扰的情况。通过数值模拟，分别得到了层流边界层和湍流边界层分离条件、壁面参数分布规律、干扰点后激波系结构及湍流边界层厚度变化趋势。结果表明，除入射激波强度外，边界层厚度也是影响湍流边界层分离的主导因素；当湍流边界层发生分离时，干扰点后的边界层可能增厚，可能不变也可能变薄；分离区近壁温度可能降低；在同一楔角的情况下，随着来流马赫数的增加，第一道和第二道反射激波的相对位置发生改变，由平行变为相交。在简单的二维平板／楔结构研究的基础上，本文还进行了超燃冲压发动机进气道内边界层分离的数值分析，为解决航空航天领域的一些工程实际问题提供了理论参考。更多还原

【Abstract】 Shock-Wave/Boundary-Layer Interaction is ubiquitous in high-speed flight, occurring in an almost limitless number of external and internal flow problems relevant to aircraft, missiles, and rockets. That the separation of boundary layer induced by shock wave causes a series of problems such as flowing block in air passage is worth studying.The separation of boundary layer induced by different intensity of impinging shock wave generated by 2D wedge/plate configuration is numerically studied in the present paper. Mach number of coming flow and wedge angle determine the intensity of shock wave. The interaction between shock waves, which are varied with Mach number of coming flow and wedge angle, and flat boundary layer is compared and analyzed.The separation conditions of laminar and turbulent boundary layer, the distribution of the parameters along wall, the configuration of shock waves and the change of thickness for turbulent boundary layer behind the interaction plot are illustrated in details. The results show, the thickness of turbulent boundary layer is the crucial factor of the state of separation, besides the intensity of impinging shock wave; the separation makes the thickness of turbulent boundary layer at the downstream zone of impinging point may increase, may equal, or may decrease; the temperature along wall surface at the impinging point may decrease; with the increase of mach number for the coming flow under the condition of the same wedge angle, the relative position of the first and the second reflection shock waves become intersecting instead of paralleling.Based on hereinbefore research, the interaction of shock wave/boundary in inlet for scramjet is simulated here. The study can be used as theoretical reference on relative issues in the field of aviation and aerospace.更多还原