Post-Shock Expansion Phenomenon in Supersonic Internal Flow

超音速内流中的激波后膨胀现象

• 批准号: 02452119
• 负责人: MATSUO Kazuyasu
• 金额: $ 4.16万
• 依托单位: KYUSHU UNIVERSITY
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for General Scientific Research (B)
• 财政年份: 1990
• 资助国家: 日本
• 起止时间: 1990 至 1992
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-02452119/
• 关键词: Supersonic flow; Shock wave; Interaction with boundary layer; Post-shock expansion; Internal flow

1. The post-shock expansion phenomenon caused by the interaction of a normal shock wave with a turbulent boundary layer in supersonic internal flows is responsible for the curviness of interacting shock, the flow blockage, and the expansion waves behind the bifurcation shock system. The post-shock expansion appears as the shock-induced separation occurs.2. The post-shock expansion becomes stronger as the flow Mach number as well as the divergence angles of the nozzle or diffuser increases. As the Mach number increases over a critical value, the post-shock expansion transforms into the pseudo-shock pattern.3. The incipient post-shock expansion occurs at nearly constant wall Mach number even the divergence angle of diffuser is varied. It implies that the concept of free interaction observed in a variety of external flows should be also applied to internal supersonic flows.4. The unsteadiness caused by the shock wave/turbulent boundary layer interaction was investigated experimentally. The frequencies of oscillating shock wave in internal flows are much lower than those in external flows. The maximum root-mean-square values of fluctuating pressures increase with an increase in flow Mach number and they are significantly affected by flow separation. A flow model of oscillating shock waves in internal supersonic flows is presented.

1.超声速内流中正激波与湍流边界层相互作用引起的激波后膨胀现象是导致相互作用激波弯曲、流动阻塞和分叉激波系统后膨胀波的原因。随着冲击诱导分离的发生，出现冲击后膨胀。2.随着来流马赫数的增大，以及喷管或扩压器扩张角的增大，激波后膨胀变得更强。当马赫数超过临界值时，激波后膨胀转变为伪激波.在壁面马赫数几乎不变的情况下，即使扩压器的扩张角发生变化，激波后的初始膨胀也会发生。这意味着在各种外部流动中观察到的自由干扰概念也应该应用于内部超声速流动。对激波/湍流边界层干扰引起的非定常流动进行了实验研究。内流中振荡激波的频率远低于外流中振荡激波的频率。脉动压力的最大均方根值随来流马赫数的增大而增大，且受流动分离的影响显著。本文提出了一个超声速内流中振荡激波的流动模型。

项目成果

金 義東: "The Post-Shock Expansion in a Supersonic Nozzle" Proceedings of the 2nd KSME-JSME Fluids Engineering Conference. 2. 52-57 (1990)

Kim, Yi-dong：“超音速喷嘴中的冲击后膨胀”第二届 KSME-JSME 流体工程会议论文集。2. 52-57 (1990)。

Heuy-Dong Kim: "Analytical Study on Post-Shock Expansion in Transonic Flow" Engineering Science Reports of Kyushu University. Vol.12,No.3. 319-328 (1990)

Heuy-Dong Kim：“跨音速流中激波后膨胀的分析研究”九州大学工程科学报告。

松尾 一泰: "Measurement of Oscillating Shock Wave in Supersonic Nozzle" Flow Visualization. 6. 612-616 (1992)

Kazuyasu Matsuo：“超音速喷嘴中振荡冲击波的测量”流动可视化。6. 612-616 (1992)

松尾 一泰: "ラインシメ-ジセンサによる衝撃波の振動の計測" 可視化情報. 11. 231-234 (1991)

Kazuyasu Matsuo：“使用线位移传感器测量冲击波振动”可视化信息。11. 231-234 (1991)

松尾 一泰: "The PostーShock Expansion in a Supersonic Nozzle" Proceedings of the and KSMEーJSME Fluid Engineering. 2. 52-57 (1990)

Kazuyasu Matsuo：“超音速喷嘴中的冲击后膨胀”和 KSME-JSME 流体工程论文集，2. 52-57 (1990)。