Research on Design Tool for the Supersonic Intake

在超声速商用飞机的发展中，关键技术是超声速发动机，其气动性能高度依赖于进气。由于激波与边界的相互作用，进气内部的流场非常复杂，不仅具有重要的工程应用意义，而且从流体物理学的角度来看也是非常有趣的。本文提出了一种计算进气流场的数值格式。该方法采用迎风TVD格式来计算激波-边界层相互作用的刚性流场。计算结果与实验结果定性吻合较好。然而，为了在定量上取得良好的一致性，湍流模型和三维处理还需要进一步的研究。研究了计算流体力学在工程设计工具中的应用。本文的主要课题是开发一种高效的网格生成方案和计算结果的后处理。这些预处理和后处理对于CFD在日常工程中的有效利用具有重要意义。进气流场的三维流动模拟研究将继续进行。为此，利用超级计算机的最新矢量和并行架构开发流求解器是必不可少的。

In the development of the supersonic commercial airplane, the key technology is the supersonic engine whose aerodynamic performance highly depends on the intake. The flow field inside of the intake is complex because of the shock-boundary interactions, and is not only important for the engineering applications but also interesting from the viewpoint of fluid physics.In the present research, a numerical scheme has been developed for computing intake flow field. The method employed the upwind TVD scheme in order to compute the stiff flow field of the shock-boundary layer interactions. The computed results showed qualitatively good agreements with the experiments. However it is also shown that further investigation is required in turbulence modeling and three-dimensional treatments for quantitatively good agreement.The application of the computational fluid dynamics to the engineering design tool is also investigated. The main subjects of this are to develop an efficient grid generation scheme and the post-processing of the computational results. These pre- and post-processing are important for the effective use of the CFD in the routine engineering works.The research will be continued on the three-dimensional flow simulations of the intake flow field. For this purpose, to develop a flow solver utilizing the up-to-date vector and parallel architecture of the supercomputer is essential.