权益分类	功能权益	普通用户	{{item.name}}会员
{{category.name}}	{{benefitItem.name}}

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

对超声速激波内流场进行了实验和数值研究，研究了超燃冲压发动机隔离段和进气道矩形通道内的伪激波现象。（1）通过彩色条纹照片和管道壁面压力脉动测量，研究了马赫数2和4的激波位置、内部结构和特性。结果表明，在均匀流动马赫数M∞= 2的情况下，方形通道内出现了具有对称几何形状的λ型PSW。当马赫数M∞= 4时，通道内出现X型PSW，并出现明显偏向顶壁或底壁的非对称流动。(2)当M ∞= 2时，PSW振荡引起的壁面压力波动主要发生在PSW的第一激波处;当M ∞= 4时，PSW振荡引起的壁面压力波动主要发生在PSW的第一激波和第二激波处 ...更多信息 . (3)用剪切敏感液晶定性显示PSW中的壁面剪切应力，用自制的剪切应力传感器定量测量PSW中的壁面剪切应力。结果表明，在马赫数为4的PSW情况下，在顶壁附面层分离区存在反向流动，顶壁分离附面层重新附着，以及PSW中壁面剪应力的大小如何变化。采用Harten-Yee二阶TVD格式和Baldwin-Lomax湍流模型进行数值模拟，计算结果表明，PSW内底壁边界层分离较明显，分离区存在回流。（4）对马赫数为2的PSW流场的计算结果与实验结果吻合较好。(5)在马赫数为4的PSW情况下，由于实验中的非对称特性，计算结果与实验结果存在一定的差异。然而，计算结果对于理解复杂的非对称现象是有价值的。少