超音速流中球头反向喷流流场的数值模拟  

NUMERICAL SIMULATION OF COUNTER FLOW SONIC NOSEJET INTO A SUPERSONIC STREAM

作　　者：马汉东[1] 周伟江[1] 

机构地区：[1]北京空气动力研究所,北京100074

出　　处：《航空学报》1993年第5期A297-A300,共4页Acta Aeronautica et Astronautica Sinica

基　　金：国家青年科学基金

摘　　要：采用CSCM(Conservative Supra-Characteristics Method)格式结合激波捕捉法求解了Navier-Stokes方程。通过算例对喷口总压等于2.08倍到6.54倍波后总压等4种情况进行了计算。得到壁面压力分布、等密度线和典型流场速度矢最图。与实验结果和其它数值计算值进行了比较和分析,得到本文计算出的弓形激波脱体距离在喷口压力低时与实验值符合得很好;压力高时差些。The flow field resulting from a sonic nosejet issuing counter to a supersonic stream is computed by using an implicit CSCM scheme and bow-shock capturing method. The Navier-Stokes equations are used in the present study. A hemisphere-cylinder submerged in a Mach 2.5 stream is analyzed. The nosejet has a nozzle diameter equal to 0.132 cylinder diameters. This configuration has a very large recirculating flow region adjacent to the jet. Under four kinds of jet pressure the features of the computed flow field are presented in detail and discussed. Comparisons of the computed pressure distributions on the nose surface with measured data and other calculation results are made and show good agreement. The attachment locations of the separated stream on the hemisphere nose are well predicted. Also the vortex rings are reasonable and shocks including Mach disks are sharply defined.

关 键 词：球柱体 反向喷流 数值模拟 流场 

分 类 号：V211.1[航空宇航科学与技术—航空宇航推进理论与工程]