Investigation on Unsteady Interaction Phenomena of Shock Waves and Turbulent Boundary Layers in Supersonic Internal Flows

超音速内流激波与湍流边界层非定常相互作用现象研究

基本信息

批准号：
16360083
负责人：
SUGIYAMA Hiromu
金额：
$ 8.32万
依托单位：
MURORAN ITSTITUTE OF TECHNOLOGY
依托单位国家：
日本
项目类别：
Grant-in-Aid for Scientific Research (B)
财政年份：
2004
资助国家：
日本
起止时间：
2004 至 2006
项目状态：
已结题

项目摘要

Experimental and numerical investigations on the supersonic internal flows with shock waves, i.e., so called Pseudo-Shock Wave ( PSW) phenomena in rectangular ducts related to scramjet engine isolators and intakes, were conducted. Experimental results are summarized as follows:(1) The location, internal structure and characteristic of the Mach 2 and 4 PSWs were investigated by color shlieren photographs and duct wall pressure fluctuation measurements. As the results, it was revealed that in the case of uniform flow Mach number M∞= 2, λ-type PSW with symmetric geometry occurs in the square duct. In the case of Mach number M∞= 4, an X-type PSW occurs in the duct, and an asymmetric flow which deviates greatly to top or bottom wall appears.(2) In the case of M_∞= 2, large wall pressure fluctuations due to the PSW oscillations occur under the first shock wave of the PSW, while in the case of M_∞= 4, the large wall pressure fluctuations occur under the first and second shock waves of the PSW … More .(3) The wall shear stresses in PSWs were visualized qualitatively by shear-sensitive liquid crystal, and measured quantitatively by the hand made shear stress transducer. As the results, it was revealed that in the case of Mach 4 PSW reverse flows exist in the top wall boundary layer separation region, and that the separated boundary layer on the top wall is reattached, and how the magnitude of the wall shear stress change in the PSW. It was also revealed that the bottom wall boundary layer separates widely in the PSW and the reverse flow exist in the separation region.Numerical simulations were carried out using the Harten-Yee second order TVD scheme and the Baldwin-Lomax turbulence model. Numerical results are summarized as follows:(4) The computational results for the Mach 2 PSW are in good agreement with the experimental results.(5) In the case of Mach 4 PSW, the several differences were found between the computational results and experiments due to asymmetric characteristics in the experiment which could not be reproduced in the simulation. However, the computational results are valuable for understanding the complex asymmetric phenomena. Less

对超音速冲压发动机隔离器和进气道中带有冲击波的内部流动，即所谓的伪冲击波（PSW）现象进行了实验和数值研究，实验结果总结如下：（1）通过彩色照片和管道壁压力波动测量研究了马赫数 2 和 4 PSW 的位置、内部结构和特性。均匀流马赫数M∞= 2 时，方形风道内出现对称几何形状的λ 型PSW。当马赫数M∞= 4 时，风道内出现X 型PSW，出现非对称流动。 (2)当M_∞=2时,PSW第一激波下由于PSW振荡而产生较大的壁面压力脉动,而在当M_∞= 4时，PSW的第一和第二冲击波下会出现较大的壁面压力脉动…… 更多。 (3) PSW中的壁面剪应力通过剪切敏感液晶定性可视化，并通过结果表明，在马赫数 PSW 的情况下，顶壁边界层分离区域存在反向流动，并且顶壁上分离的边界层重新附着，以及PSW中壁面剪应力的大小如何变化还揭示了PSW中底壁边界层发生广泛分离并且分离区域中存在逆流。利用Harten-Yee第二模型进行了数值模拟。阶TVD格式和Baldwin-Lomax湍流模型的数值结果总结如下：(4)马赫数PSW的计算结果与实验结果吻合得很好。(5)在马赫数的情况下。 4 PSW，由于实验中的不对称特性，计算结果与实验之间存在一些差异，这些差异无法在模拟中重现，但是，计算结果对于理解复杂的不对称现象很有价值。