"A Study on Shock Wave Self-Excited Oscillation in Supersonic Flows"

“超音速流中冲击波自激振荡的研究”

• 批准号: 08405063
• 负责人: ASO Shigeru
• 金额: $ 20.48万
• 依托单位: KYUSHU UNIVERSITY
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (A)
• 财政年份: 1996
• 资助国家: 日本
• 起止时间: 1996 至 1998
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-08405063/
• 关键词: Shock wave; Self-Occilation; Supersonic flow; Aerodynamic heating; Supersonic mixing; Cavity flow; Opposing jet; Plug nozzle; キャビテイ流; 非定常流; 干渉場; 非平衡; 超音速混合流

The purpose of the present study is to investigate the shock wave self-excited oscillation in supersonic flows. Hence, many supersonic flows with shock waves have been experimentally and computationally studied. The emphasis is based on the physical understanding of the flow structure and flow physics of shock wave self-excited oscillation in supersonic flows. For the research projects eight topics are selected and studied in the present study as follows and the objectives of the present study have been completed. :(1) Self-induced oscillation of shock wave in shock wave/turbulent boundary layer have been studied. The flow separation is not uniform and quite unsteady. Also the unsteady features are independent on mach number. The new flow visualization technique by LIF is installed for the measurement of density contour.(2) Self-induced oscillation of shock wave in opposing jet in supersonic flow have been studied. Numerical simulations show quite good agreement with experiments. Measu … More red pressure fluctuations show that dominant frequency changes due to total pressure of jet.(3) Interacting flow field between supersonic jet and wall has been studied. The interacting flow pattern and shock wave oscillation pattern changes drastically due to the distance between the nozzle exit and wall.(4) The supersonic mixing flow fields have been studied. Numerical simulations have been also conducted resulting quite good agreement with experiments. The new technique for supersonic mixing has been proposed and demonstrated its capability.(5) Shock wave induced aerodynamic heating has been studied with thermally and chemically nonequilibrium conditions. High temperature effects on aerodynamic heating have been revealed.(6) Aerodynamic haeting problems generated from shock wave ahead of the blunt body have been studied. Film cooling has proved to have sufficient capability for reducing aerodynamic heating.(7) Cavity flow generated by the gap of the tile of the reentry vehicle has been studied with peak pressure and peak heating. Oscillatory cavity flows with embedded shock waves have been captured.(8) Supersonic flows with embedded shock wave around plug nozzle have been studied. The effect of the shape of plug nozzle on the drag is investigated and the drastic reduction of the drag is obtained by optimal nozzle shape. Less

本研究的目的是研究超音速流中的冲击波自激发振荡。因此，许多带有冲击波的超音速流经过实验和计算研究。重点是基于对超音速流中冲击波自激发振荡的流动结构和流动物理的物理理解。对于研究项目，在本研究中选择并研究了八个主题，如下所示，本研究的目标已经完成。 ：（1）冲击波/湍流边界层中的冲击波的自我振荡已经研究了。流动分离不是统一的，也不固定。同样，不稳定的功能在马赫数上是独立的。安装了LIF的新流动可视化技术，以测量密度轮廓。（2）已研究了超音速流中对方喷气的自我引起的冲击波振荡。数值模拟与实验相当一致。测量…更多的红压波动表明，由于射流的总压力而导致的主要频率变化。（3）超音速射流和壁之间的相互作用流场已经研究了。由于喷嘴出口和壁之间的距离，相互作用的流动模式和冲击波振荡模式发生了巨大变化。（4）超音速混合流场已经研究了。还进行了数值模拟，与实验相当一致。已提出了超音速混合的新技术并证明了其能力。（5）冲击波诱导的空气动力学加热已经使用了热和化学上的非平衡条件进行了研究。已经揭示了对空气动力学加热的高温影响。（6）在钝体之前由冲击波产生的空气动力学讨厌问题已经研究了。事实证明，膜冷却具有足够的能力，可以减少空气动力学加热。（7）通过峰值压力和峰值加热，由重新进入车辆的间隙产生的腔流量已经研究了。已经捕获了带有嵌入式冲击波的振荡腔流。（8）已研究了带有插头喷嘴的嵌入式冲击波的超音速流。研究了插头喷嘴形状对阻力的影响，并通过最佳喷嘴形状获得阻力的阻力。较少的

项目成果

T.Minota,M.Nishida and G.Lee: "Shock Waves Generated by the Interaction of Two Vortex Rings" Proc.20th Int.Symp.on Shock Waves. Vol.I. 563-568 (1996)

T.Minota、M.Nishida 和 G.Lee：“两个涡环相互作用产生的冲击波”Proc.20th Int.Symp.on 冲击波。

Kazuyuki UMII, Shigeru ASO et. al.: "A Study on Three-Dimensional Supersonic Mixing Flow Phenomena" 20th International Symposium on Shock Waves, held at Pasadina, CA, U.S.A on July 23-28, 1995. Vol.1. 355-360 (1996)

UMII 和之、麻生茂等

M.Hirakawa, S.Aso, M.Nishida and M.Matsumo: "Arc-Heated Wind Tunnel Experiments" Proc. 2nd Asian-Pacific Conf. On Aerospace Technology and Science. held at Dun Huang, China,on September, 1997. 125-130 (1997:)

M.Hirakawa、S.Aso、M.Nishida 和 M.Matsumo：“电弧加热风洞实验”Proc。

Shigeru ASO et. al.: "A Study on Supersonic Mixing Flowfield with Swept Ramp Injectors" Proceedings of 35th AIAA Aerospace Sciences Meeting and Exhibit, AIAA 97-0397, held on January 6-9,1997, at Reno, Nevada, USA. (1997)

麻生茂等。

辛島桂一、麻生 茂、中村和義、神下 誠: "超音速流中の逆噴射ジェットの流れ場に関する実験的研究" 日本航空宇宙学会西部支部講演会講演集. 18-21 (1998)

Keiichi Karashima、Shigeru Aso、Kazuyoshi Nakamura、Makoto Kamishita：“超音速流中反向喷射流场的实验研究”日本航空学会西部分会会议记录 18-21（1998）。