Analysis of Shock Wave System with Composed Structure Induced by Near Field Collision between Supersonic Jet and Solid Wall

超音速射流与固体壁近场碰撞复合结构冲击波系统分析

基本信息

批准号：
14550169
负责人：
KASHIMURA Hideo
金额：
$ 2.5万
依托单位：
Kitakyushu National College of Technology
依托单位国家：
日本
项目类别：
Grant-in-Aid for Scientific Research (C)
财政年份：
2002
资助国家：
日本
起止时间：
2002 至 2004
项目状态：
已结题

来源：
https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-14550169/
关键词：
Supersonic Jet Collision Jet Shock Wave Mach Disk Plate Shock Wave Separation Babble Recirculation Flow

项目摘要

The numerical calculation using the TVD method and the experimental analysis of flow visualization and measurements of wall temperature are carried out, and discussed the generation mechanism of the temperature peak. Next, We try to control the pressure wave induced by surface conditions. The conclusions are summarized as follows.(1) The flow velocity and the position and numbers of stagnation point are complexly changes by the existence of the separation bubbles.(2) The pressure distribution on the wall changes by the separation bubble, and the locally pressure peak are occurred when the separation bubble is generated. The positions of pressure peak are dependent on the non-dimensional distance of wall and pressure ratio.(3) The position of the Mach disk in the jet moves to upper side and diameter is extend rather than free jet. The pressure behind the Mach disk is increment than the free jet.(4) The maximum temperature and pressure on the wall are generated near the cross point of wall and axis of the jet, and the secondly peaks of temperature and pressure is generated by the separation bubble. These position of peak condition are influence by the self induced oscillation.(5) The time average pressure at the cross position of the jet are decrease for increment of the pressure ration and the position of plate.(6) The changes of boundary layer curvature is observed at the interaction point of the upper and lower tail shock waves with the inclined wall and it is due to the generation of separation bubble.(7) The peak temperature on the axis of inclined surface is generated due to the change of thickness of boundary layer together with the temperature peak occur by the shock wave interacted with wall.(8) The temperature along the nozzle axis are increases with the increment of roughness of surface.

进行了TVD方法的数值计算、流动可视化和壁温测量的实验分析，并讨论了温度峰值的产生机制。接下来，我们尝试控制由表面条件引起的压力波。主要结论如下：(1)分离气泡的存在使流速、驻点的位置和数量发生复杂的变化。(2)分离气泡的存在使壁面压力分布发生变化，局部压力分布发生变化。当分离气泡产生时，出现压力峰值。压力峰值的位置取决于壁面无量纲距离和压力比。(3)射流中马赫盘的位置向上移动，直径扩大而不是自由射流。马赫盘后面的压力比自由射流有所增加。(4)壁面上的最大温度和压力产生在壁面与射流轴线的交叉点附近，第二个峰值温度和压力由射流产生。分离气泡。这些峰值条件的位置受到自激振荡的影响。(5)射流交叉位置的时间平均压力随着压力比和板位置的增加而减小。(6)边界层曲率的变化在上下尾部激波与斜壁的相互作用点观察到，这是由于分离气泡的产生而产生的。(7) 斜面轴上的峰值温度是由于斜壁厚度的变化而产生的。边界层以及由冲击波相互作用产生的温度峰值(8)沿喷嘴轴线的温度随着表面粗糙度的增加而增加。