Study of Oscillation Characteristics of Shock Trains Formed in Supersonic Internal Flow and its Suppressing Method

超音速内流激波列振荡特性及抑制方法研究

• 批准号: 13450078
• 负责人: MATSUO Kazuyasu
• 金额: $ 8.58万
• 依托单位: University of Kitakyushu (2002-2003)Kyushu University (2001)
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (B)
• 财政年份: 2001
• 资助国家: 日本
• 起止时间: 2001 至 2003
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-13450078/
• 关键词: supersonic flow; shock train; pseudo-shock wave; shock; boundary layer interaction; flow oscillation; 境界層干渉

(1)Shock trains and pseudo-shocks have been formed insupersonic internal duct flows due to the interaction between a normal shock wave and a turbulent boundary layer. The three dimensional flow structure of the shock trains and pseudo-shocks has been investigated numerically and experimentally, and the complicated shock structure was made clear.(2)Multiple shocklets generated in a two-dimensional transonic diffuser was observed with a high speed camera combined with schlieren method, and the motions of each shock wave have been recorded. The experimental results were compared with the calculated values assuming a pressure disturbance given by the sine function at the channel exit, and it is shown that the experiments agree well with the calculated results.(3)From the above study, it is concluded that the multiple shocklet pattern appears when the amplitude of disturbance is not large and the diverging part of the channel downstream of the ordinary shock wave is long.(4)The self-excited shock wave oscillation in two-dimensional supersonic and transonic diffusers was investigated experimentally. The results show that a pressure disturbance is generated near the stem of the shock wave and it moves downstream. In the downstream region where the boundary layer becomes highly turbulent, another disturbance is generated and it causes the shock wave oscillation.

(1)正常激波与湍流边界层相互作用，在超音速管道内流动中形成激波列和拟激波。通过数值和实验研究了激波串和伪激波的三维流动结构，揭示了复杂的激波结构。(2)利用高速摄像机结合纹影方法观测了二维跨声速扩散器中产生的多个激波，并记录了每个激波的运动。实验结果与假定通道出口处正弦函数给出的压力扰动的计算值进行了比较，实验结果与计算结果吻合较好。(3)通过以上研究，得出了当扰动幅度不大且普通激波下游通道发散部分较长时，出现多激波图形的结论。(4)对二维超音速和跨音速扩散器中的激波自激振荡进行了实验研究。结果表明，在激波尖端附近产生压力扰动，并向下游移动。在附面层高度湍动的下游区域，会产生另一种扰动，并引起激波振荡。

项目成果

T.Handa: "Formation of Multiple Shocklets in a Transonic Diffuser Flow"Shock Waves - An International Journal. 11. 423-430 (2002)

T.Handa：“跨音速扩散器流中多个冲击波的形成”冲击波 - 国际期刊。

半田太郎: "衝撃波を含むダクト内超音速流れ場の数値解析"九州大学情報基盤センター年報. 2. 35-44 (2002)

半田太郎：“包含冲击波的管道中超音速流场的数值分析”九州大学信息技术中心年度报告2. 35-44（2002）。

T.Handa: "Formation of Multiple Shocklets in a Transonic Diffuser Flow"Shock Waves-An International Journal. 11. 423-430 (2002)

T.Handa：“跨音速扩散器流中多个冲击波的形成”冲击波-国际期刊。

K.Matsuo: "Structure of Shock Trains in Constant Area Ducts"Experimental Heat Transfer, Fluid Mechanics, and Thermodynamics. 3. 1859-1864 (2002)

K.Matsuo：“恒定面积管道中冲击列车的结构”实验传热、流体力学和热力学。

Taro Handa, et al.: "Formation of Multiple Shocklets in a Transonic Diffuser Flow"Shock Waves -An International Journal. Vol.11. 423-430 (2002)

Taro Handa 等人：“跨音速扩散流中多个冲击波的形成”冲击波 - 国际期刊。