| 采用新型基准流场的高超声速内收缩进气道性能分析 |
| |
| 引用本文： | 南向军,张堃元.采用新型基准流场的高超声速内收缩进气道性能分析[J].宇航学报,2012(2):254-259. |
| |
| 作者姓名： | 南向军 张堃元 |
| |
| 作者单位： | 南京航空航天大学能源与动力学院 |
| |
| 基金项目： | 国家自然科学基金(90916029) |
| |
| 摘 要： | 通过改变中心体形状,设计了新型轴对称基准流场,可显著降低反射激波强度,明显提高压缩效率。基于该基准流场和传统基准流场,分别设计了两个圆形出口内收缩进气道,并对二者的流场及总体性能进行了数值研究。结果表明,新的进气道设计点和接力点肩点附近激波附面层相互作用减弱,流场结构优于传统进气道,压缩效率明显提高,同时进气道起动性能得到改善。
|
| 关 键 词： | 高超内收缩进气道 基准流场 数值模拟 |
Analysis of Hypersonic Inward Turning Inlet with Innovative Axisymmetric Basic Flowfield |
| |
| Institution: | NAN Xiang-jun,ZHANG Kun-yuan(College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China) |
| |
| Abstract: | An innovative basic flowfield is designed and studied by using a controlled centre body to weak the reflection shock wave and increase the compression efficiency.Two circular inward turning inlets with new and old basic flowfileds are designed and numerically studied.The results indicate,compared with the old inlet,the new one has weaker cowl shock wave/boundary layer interaction,better flowfield,higher compression efficiency,and better start performance. |
| |
| Keywords: | Hypersonic inward turning inlets Basic flowfield Numerical simulation |
| 本文献已被 CNKI 等数据库收录！ |
|
