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，关键技术是超音速发动机，其气动性能很大程度上取决于进气量。由于激波边界相互作用，进气口内部的流场非常复杂，不仅对于工程应用很重要，而且从流体物理学的角度来看也很有趣。在本研究中，已经开发了一种计算进气口的数值方案流场。该方法采用迎风 TVD 方案来计算激波-边界层相互作用的刚性流场。计算结果与实验结果在质量上表现出良好的一致性。然而，研究还表明，在湍流建模和三维处理方面还需要进一步研究，以获得良好的定量一致性。还研究了计算流体动力学在工程设计工具中的应用。其主要课题是开发有效的网格生成方案和计算结果的后处理。这些前处理和后处理对于CFD在日常工程中的有效应用具有重要意义。今后将继续研究进气流场的三维流动模拟。为此，开发利用超级计算机最新矢量和并行架构的流求解器至关重要。

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。

楠井 徹郎,中橋 和博,藤井 昭一: "スイ-プを伴う翼列の粘性流数値解析" 日本機械学会関西支部第66期定時総会講演論文集. (1991)

Tetsuro Kusui、Kazuhiro Nakahashi、Shoichi Fujii：“扫掠叶栅中粘性流的数值分析”日本机械工程师学会关西分会第 66 届年会论文集（1991 年）。

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)。