Research on Design Tool for the Supersonic Intake

超音速进气道设计工具研究

• 批准号: 01550050
• 负责人: NAKAHASHI Kazuhiro
• 金额: $ 1.22万
• 依托单位: University of Osaka Prefecture
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for General Scientific Research (C)
• 财政年份: 1989
• 资助国家: 日本
• 起止时间: 1989 至 1990
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-01550050/
• 关键词: Aero engines; CFD; Shock-Boundary Layer Interaction

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.

在超音速商用飞机的研制中，超音速发动机是关键技术，而进气道对发动机的气动性能有很大的影响。由于激波与边界层的相互作用，进气道内的流场是一个复杂的流场，不仅具有重要的工程应用价值，而且从流体物理的角度来看也是一个有趣的问题。该方法采用迎风TVD格式计算激波-边界层干扰的刚性流场。计算结果与实验定性吻合良好。然而，它也表明，需要进一步的研究，在湍流模型和三维处理的定量良好的协议。应用计算流体动力学的工程设计工具进行了研究。本研究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。这些前、后处理工作对CFD在日常工程中的有效应用具有重要意义。为此，开发一个流动求解器，利用最新的矢量和并行结构的超级计算机是必不可少的。

项目成果

K. Nakahashi: ""Optimum Spacing Control of Marching Grid Generation"" AIAA Paper. 91-0103. (1991)

K. Nakahashi：“行进网格生成的最佳间距控制”AIAA 论文。

中橋 和博(分担執筆) (日本航空宇宙学会編): "第二版航空宇宙工学便覧" 丸善株式会社,

中桥一宏（撰稿人）（日本航空学会编）：《第2版航空航天工学手册》丸善株式会社

K. Nakahashi: ""A Marching Grid Generation"" Proc. of 4th CFD Symposium. 491-494 (1990)

K. Nakahashi：“前进的网格一代”Proc。

中橋 和博: "格子幅の最適制御" 第22回流体力学講演会講演集. 64-67 (1990)

Kazuhiro Nakahashi：“网格宽度的优化控制”第 22 届流体力学会议论文集 64-67 (1990)。

Kazuhiro Nakahashi Kouichi Egami: "Unstructured Upwind Approach for Complex Flow Computations" Lecture Notes in Physics(Springu・Verlag) (12th Int.Conf.Numerical Methods in Fluid Dynamics). (1991)

Kazuhiro Nakahashi Kouichi Egami：“复杂流动计算的非结构化迎风方法”物理学讲义（Springu・Verlag）（第 12 届 Int.Conf.流体动力学数值方法）（1991 年）。