Study on Aerodynamic Noise induced by Shock Waves in Supersonic Flows and Development of a Method for Reducing the Noise

超音速流中冲击波气动噪声的研究及降噪方法的开发

• 批准号: 09450080
• 负责人: MATSUO Kazuyasu
• 金额: $ 8.64万
• 依托单位: KYUSHU UNIVERSITY
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (B)
• 财政年份: 1997
• 资助国家: 日本
• 起止时间: 1997 至 1999
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-09450080/
• 关键词: shock wave; supersonic flow; aerodynamic noise; supersonic jet; supersonic nozzle

1. The oscillations of the normal shock waves in supersonic nozzles and supersonic diffusers were investigated using a supersonic wind tunnels, and a strong correlation were found among the shock oscillation, the static pressure fluctuation on the wall, and the generated aerodynamic noise.2. Small pressure disturbances which are generated and propagated upstream from downstream portion of the shock wave were observed, and it was found that these disturbances induce the shock oscillation. At the downstream portion, the boundary layer behaves unsteadily and violently. Also, vortices generated by the shock oscillation were observed to be convected downstream. Based on these results, the shock oscillation was explained to be sustained by the upstream-propagating disturbances and the downstream-convected vortices.3. The response of a normal shock wave to a white small pressure disturbance having the same power spectral density in the supersonic diffuses was analyzed, and it was shown that the shock displacement spectral density distributions obtained by the analysis agree very well with those measured in the present and previous experimental data.4. Theoretical and experimental investigations were performed on the structures of correctly-expanded and under-expanded supersonic laminar and turbulent jets, and the distributions of the Pivot impact pressure and flow turbulence in the jets, the length of the potential core, the condition of the generation of shock waves and their locations in the jets were made clear.5. The flow mechanism on the distributions of the Pitot impact pressure along the center line of the jet was well explained, and the correlation between the aerodynamic noise level and the correctly and under expanded supersonic jets.

1。使用超音速风隧道研究了超音速喷嘴和超音速扩散器中正常冲击波的振荡，并在冲击振荡，壁上的静压波动和产生的空气动力学噪声中发现了很强的相关性。2。观察到了冲击波下游部分产生并在上游传播的小压力干扰，发现这些干扰会引起冲击振荡。在下游部分，边界层的行为不稳定和猛烈。同样，观察到由冲击振荡产生的涡旋在下游。基于这些结果，解释的冲击振荡被上游传播的干扰和下游感染的涡流所维持。3。分析了在超音速扩散中具有相同功率谱密度的白色小压力干扰的正常冲击波对超音频谱密度相同的响应，并表明通过分析获得的休克位移光谱分布与当前和先前的实验数据中测量的响应非常吻合。4。对理论和实验研究进行了对正确扩展和膨胀不足的超音速层层和湍流喷气机的结构，以及枢轴冲击压力的分布和电势芯的长度，潜在核心的长度，冲击波的产生状态及其位置的生成及其位置及其位置清晰。5。很好地解释了皮托撞击压力的分布的流量机理，并且很好地解释了空气动力学水平与正确膨胀的超音速射流之间的相关性。

项目成果

Taro Handa: "Fine structure on shock oscillation in supersonic nozzle"Proc,of 4th KESM-JSME Fiuid Eng,Conf.. 445-448 (1998)

半田太郎：“超音速喷嘴冲击振荡的精细结构”Proc,of 4th KESM-JSME Fiuid Eng,Conf.. 445-448 (1998)

Taro Handa: "Fine structure on shock oscillation in supersonic nozzle" Proc.of 4th KSME-JSME Fluid Eng.Conf.445-448 (1998)

半田太郎：“超音速喷嘴中冲击振动的精细结构”Proc.of 4th KSME-JSME Fluid Eng.Conf.445-448 (1998)

樫谷 賢士: "軸対称ノズルからの適正膨張超音速層流噴流の構造"日本機会学会論文集. 63・616. 3905-3912 (1999)

Kenji Kashitani：“来自轴对称喷嘴的适当扩展的超音速层流射流的结构”，日本机械工程师学会会刊 63・616（1999 年）。

則松 康文: "スートブロア用超音速ノズル噴流の可視化計測とピトー圧分布"九州大学総合理工学研究科報告. 21・3. 289-294 (1999)

Yasufumi Norimatsu：“吹灰器超音速喷嘴射流的可视化测量和皮托压力分布”九州大学理工学院报告21・3（1999）。

片野田 洋: "軸対称超音速自由噴流の数値シュミレーション"九州大学総合理工学研究科報告. 20・1. 13-18 (1998)

片田浩：“轴对称超音速自由射流的数值模拟”九州大学研究生院理工学研究报告20・1（1998）。