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| 1 | Numerical Study for Hysteresis Phenomena of Shock Wave Reflection in Overexpanded Axisymmetric Supersonic Jet显示文摘当高压的气体对从超声的嘴的真空房间精疲力尽时, overexpanded 超声的喷气以特定的状况被形成。在二维的超声的喷气,而且,为流动地里的冲击波的思考类型的磁滞现象现象在伪稳定的流动下面并且例如被发生,这被知道,在常规思考( RR )和马赫思考(先生)之间的过渡压力比率被这现象影响。许多报纸为 underexpanded 描述了磁滞现象现象在 overexpanded axisymmetric 喷气下面的超声的喷气,而是这现象没在过去的报纸被详细说明。这研究的目的是用 TVD 方法在 overexpanded axisymmetric 喷气为冲击波的思考类型清除磁滞现象现象并且讨论磁滞现象现象的特征。 | Tsuyoshi Yasunobu Ken Matsuoka Hideo Kashimura ShigeruMatsuo ToshiakiSetoguchi | 2006 | Journal of Thermal Science2006，15，3： | 1 |
| 2 | Effect of Plate Position and Size for Self-Induced Flow Oscillation of Underexpanded Supersonic Jet Impinging on Perpendicular Plate显示文摘When the underexpanded supersonic jet impinges on the obstacle, it is well known that the self-induced flow oscillation occurs at the specific condition of the pressure ratio in the flowfield, the position of an obstacle and so on. This oscillation is related with the noise problems of aeronautical and other industrial engineering so that the characteristic and the mechanism of self-induced flow oscillation have to be cleared to control the various noise problems. But, it seems that the characteristics of the oscillated flowfield and the mechanism of oscillation have to be more clear to control the oscillation. This paper aims to clarify the effect of the plate position and the width for the self-induced flow oscillation of an underexpanded supersonic jet impinging on the perpendicular plate by the experiment and the numerical analysis. From the results, it is clear that the occurring domain of the self-induced flow oscillation and its dimension strongly depend on the plate position and the width. | Tsuyoshi Yasunobu Yumiko Otobe Hideo Kashimura | 2011 | Journal of Thermal Science2011，20，3： | 1 |
| 3 | Self-Induced Oscillation of Supersonic Jet DuringImpingement on Cylindrical Body显示文摘The phenomena of the interaction between a supersonic jet and an obstacle are related to the problems of the aeronautical and other industrial engineerings. When a supersonic jet impinges on an obstacle,the self induced oscillation occurs under several conditions. The flow characteristics caused by the im-pingement of underexpanded supersonic jet on an obstacle have been investigated. However, it seems that the mechanism of self induced oscillation and the factor which dominates it have not been detailed in the published papers. The characteristics of the self induced oscillation of the supersonic jet during the impingement on a cylindrical body are investigated using the visualization of fiow fields and the numerical calculations in this study. | Hideo Kashimura Tsuyoshi Yasunobu(Department of Control and Information Systems Engineering, Kitakyushu College of Technology,5-20-1, Sii, Kokuraminami-ku, Kitakyushu, 803-0985, Japan)Toshiaki Setoguchi(Department of Mechanical Engineering, Saga Univers | 1998 | Journal of Thermal Science1998，7，1： | 1 |
| 4 | Discharge of a Shock Wave from an Open End of a Tube显示文摘When a Pressure wave propagates along a constant area straight tube and reaches at the open end, an impulsive wave is emitted outward from the tube exit toward the surrounding area and causes an impulsive noise like a sonic boom. In order to clarify the magnitude of an impulsive wave obtained by the discharge of a weak shock wave born an open end of a tube in relation to the noise problem and the industrial devices, the experimental and numerical investigations have been carried out for various strength of a shock wave. A simple open end shock tube with the flange at the tube exit.was used and the numerical calculation using the TVD scheme was performed. The effective equations which concerns with the magnitude of an impulsive wave generated by the emission of a shock wave have been obtained from the procedure of the open end correction based on the aeroacoustic theory and the numerical results. The influence of open end correction length and the diameter of a flange on the magnitude of an impulsive wave has been discussed. | Hideo Kashimura Tsuyoshi Yasunobu Hiroyasu Nakayama Toshiaki Setogucki Kazuyasu Matsuo | 2000 | Journal of Thermal Science2000，9，1： | 1 |
| 5 | Shock Wave in Supersonic Moist Air Jet for a Low Pressure Ratio显示文摘In the present study,a computational fluid dynamics work was performed to investigate the occurrence of the shock wave by condensation in supersonic moist air jet.The unsteady,compressible axisymmetric Navier-Stokes equation is solved by TVD(Total Variation Diminishing) scheme in this study.The numerical simulations have been performed for low pressure ratio and various humidities.The results show the occurrence of the shock wave in supersonic moist air jet for a low pressure ratio when Mach disk does not occur,depending on humidity of the air. | Yumiko OTOBE Hideo KASHIMURA Toshiaki SETOGUCHI | 2011 | Journal of Thermal Science2011，20，4： | 1 |
| 6 | Effect of Axisymmetric Sonic Nozzle Geometry on Characteristics of Supersonic Air Jet显示文摘The effect of nozzle geometry on sonic line and characteristics of supersonic air jet was studied. Computational fluid dynamics was applied in this study. The axisymmetric nozzle geometries investigated were two different contour converging nozzles, two different conically converging sharp-edged nozzles and a sharp-edged orifice. The results show that the supersonic jet structure, sonic line and streamlines in supersonic jet are strongly influenced by the nozzle geometry, and the total pressure loss increases with the increase of Mach disk diameter. The present numerical simulation is an effective tool to evaluate compressible flows in supersonic air jet. | Shigeru MATSUO Masanori TANAKA Yumiko OTOBE Hideo KASHIMURA Heuy-Dong KIM Toshiaki SETOGUCHI | 2004 | Journal of Thermal Science2004，13，2： | 1 |
| 7 | Characteristics of Spherical Shock Wave and Circular Pulse Jet Generated by Discharge of Propagating Shock Wave at Open End of Tube显示文摘When the shock wave propagating in the straight circular tube reaches at the open end, the impulsive wave is generated by the emission of a shock wave from an open end, and unsteady pulse jet is formed near the open end behind the impulsive wave under the specific condition. The pulse jet transits to spherical shock wave with the increase in the strength of shock wave. The strength is dependent on the Mach number of shock wave, which attenuates by propagation distance from the open end. In this study, the mechanism of generating the unsteady pulse jet, the characteristics of the pressure distribution in the flow field and the emission of shock wave from straight circular tube which has the infinite flange at open end are analyzed numerically by the TVD method. Strength of spherical shock wave, relation of shock wave Mach number,distance decay of spherical shock wave and directional characteristics are clarified. | Tsukasa Irie Tsuyoshi Yasunobu Hideo Kashimura Toshiaki Setoguchi Kazuyasu Matsuo | 2003 | Journal of Thermal Science2003，12，3： | 0 |
| 8 | Numerical Analysis of Turbulent Sonic Jets from Two-Dimensional Convergent Nozzles显示文摘The numerical analysis of a turbulent sonic jet from a two-dimensional convergent nozzle has been carried out using the compressible k-? turbulence model and TVD finite difference scheme. Numerical conditions have been varied over a range of operating pressure ratios from 1.893 to 6.0 which cover the jet flow conditions from correctly expanded to underexpanded. Numerical flow visualization of sonic jet structure using the computer schlieren, a relation between shock cell length in the jet with the operating pressure ratio and the pressure distribution along jet centerline are obtained. Also, a transition process of a two-dimensional sonic jet from correctly expanded to underexpanded conditions is shown in detail and a flow model of jet structure is proposed. | Hideo KASHIMURA Yuya MASUDA Yoshiaki MIYAZATO Kazuyasu MATSUO | 2011 | Journal of Thermal Science2011，20，2： | 0 |
| 9 | Characteristic and Mechanism of Pressure Fluctuation Caused by Self-Induced Oscillation of Supersonic Impinging Jet显示文摘When the underexpanded supersonic jet impinges on the obstacle, it is well known that the self-induced flow oscillation occurs. This oscillation depends on the pressure ratio in the flowfield, the position of an obstacle and is related with the noise problems of aeronautical and other industrial engineering. The characteristic and the mechanism of self-induced flow oscillation, have to be clarified to control various noise problems. But, it seems that the characteristics of the oscillated flowfield and the mechanism of an oscillation have to be more cleared to control the oscillation. This paper aims to clarify the effect of the pressure ratio and the obstacle position and the mechanism of self-induced flow oscillation by numerical analysis and experiment, when the underexpanded supersonic jet impinges on the cylindrical body. From the result of this study, it is clear that occurrence of the self-induced flow oscillation depends on the pressure balance in the flowfield. | Tsuyoshi Yasunobu Yumiko Otobe Hideo Kashimura | 2013 | Journal of Thermal Science2013，22，2： | 0 |
| 10 | Generation of Overpressure due to Condensation in Moist Air Jet显示文摘在现在的学习,一个计算液体动力学方法被使用了在下面膨胀的声音的喷气结构上以水库状况调查过度饱和的起始的度的效果,例如马赫磁盘地点和直径,桶冲击波和喷气边界。调查的 axisymmetric 嘴几何学是有直部分的一张收敛的嘴。作为结果,过压由于冷凝作用产生,这被发现,没有冷凝作用,有过压的产生的流动的特征与那些由于在喷气的冷凝作用不同。 | Yumiko OTOBE Hideo KASHIMURA Shigeru MATSUO Masanori TANAKA Toshiaki SETOGUCHI | 2007 | Journal of Thermal Science2007，16，2： | 0 |
| 11 | A Study of Under-expanded Moist Air Jet Impinging on a Flat Plate显示文摘当气体通过在的一张会聚的嘴膨胀时比率对停滞压力周围比批评的,从嘴的发出的喷气是下面膨胀的的高。如果一个扁平的盘子是到在从嘴的某个距离的喷气的放的正常,一个分开的冲击波在在嘴出口和板之间的一个区域被形成。一般来说,有非平衡冷凝作用的超声的潮湿的空气喷气技术很经常被用于工业生产过程。尽管有在侵犯到稳固的身体的超声的潮湿的空气喷气的主要特征的重要性,它的质的特征不令人满意地被知道。在现在的学习,在一个垂直扁平的盘子上侵犯的下面膨胀的空气喷气上的非平衡冷凝作用的效果与非平衡冷凝作用在情况中数字地被调查,没有非平衡冷凝作用,为流动领域的摆动的频率变得比那大,并且静态的压力的振幅干燥空气与那些相比变得小。而且,数字结果与试验性的相比。关键词可压缩的流动 - 非平衡冷凝作用 - 侵犯喷气 - 模拟 CLC 数字 | Yumiko OTOBE Shigeru MATSUO Masanori TANAKA Hideo KASHIMURA Heuy-Dong KIM Toshiaki SETOGUCHI | 2005 | Journal of Thermal Science2005，14，4： | 0 |
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