| 四段修型弥散反射激波中心体基准流场研究 |
| |
| 引用本文： | 李永洲,张堃元,钟启涛.四段修型弥散反射激波中心体基准流场研究[J].航空动力学报,2014,29(9):2055-2062. |
| |
| 作者姓名： | 李永洲 张堃元 钟启涛 |
| |
| 作者单位： | 南京航空航天大学 能源与动力学院, 南京 210016;南京航空航天大学 能源与动力学院, 南京 210016;南京航空航天大学 能源与动力学院, 南京 210016 |
| |
| 基金项目： | 国家自然科学基金（90916029，91116001，11102087） |
| |
| 摘 要： | 针对高超声速内收缩进气道宽马赫数范围工作的要求,设计了一种四段修型弥散反射激波中心体基准流场,可明显提高基准流场来流马赫数高于设计点来流马赫数(6.0)时的压缩效率,巡航点(来流马赫数为7.0)出口总压恢复系数较下凹圆弧中心体基准流场提高了2.3%.此外,基于两种基准流场分别设计了圆形进口内收缩进气道并在来流马赫数为5.0~8.0范围内进行数值计算,结果表明:来流马赫数高于设计点来流马赫数时,四段修型进气道的压缩效率更高.有黏条件下,来流马赫数为8.0时二者的增压比近似相等,四段修型进气道喉道截面出口总压恢复系数相对提高了1.1%.
|
| 关 键 词： | 高超声速 基准流场 中心体 宽马赫数范围 内收缩进气道 |
| 收稿时间： | 2013/6/13 0:00:00 |
Investigation of basic flowfield with center body consisting of four spline curves diffusing reflected shock wave |
| |
| LI Yong-zhou,ZHANG Kun-yuan and ZHONG Qi-tao.Investigation of basic flowfield with center body consisting of four spline curves diffusing reflected shock wave[J].Journal of Aerospace Power,2014,29(9):2055-2062. |
| |
| Authors: | LI Yong-zhou ZHANG Kun-yuan and ZHONG Qi-tao |
| |
| Affiliation: | College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
| |
| Abstract: | A basic flowfield with center body consisting of four spline curves diffusing reflected shock wave was designed to meet the operation requirement of the hypersonic inward turning inlet in a wide Mach number range. The compression efficiency increased obviously when the incoming flow Mach number was higher than that of the design point(6.0), and the exit total pressure recovery coefficient increased by 2.3% compared with the basic flowfield with concave arc center body at cruise point(incoming flow Mach number of 7.0). Besides, the inward turning inlets with circular shape intake were designed based on these two categories of basic flowfield. The numerical simulation results from the incoming flow Mach number of 5.0-8.0 indicate that the four spline curves inlet has higher compression efficiency when the incoming flow Mach number is higher than that of the design point. The pressure ratio is approximately equal while the throat exit total pressure recovery coefficient of four spline curves inlet increases by 1.1% when the incoming flow Mach number of 8.0 under viscous condition. |
| |
| Keywords: | hypersonic basic flowfield center body wide Mach number range inward turning inlet |
| 本文献已被 CNKI 等数据库收录！ |
| 点击此处可从《航空动力学报》浏览原始摘要信息 |
|
点击此处可从《航空动力学报》下载全文 |
|
