反向喷流与主流干扰数值模拟  

Numerical Simulation of the Interaction Between a Supersonsic stream and Countering Nosejet

作　　者：周伟江[1] 马汉东[1] 李锋[1] 邓宁丰[1] 

机构地区：[1]北京空气动力研究所

出　　处：《空气动力学学报》1994年第3期295-300,共6页Acta Aerodynamica Sinica

基　　金：国家青年自然基金

摘　　要：　反向喷流是改变钝体迎风面压力和温度分布的有效手段之一，所以了解反向喷流流场对再入体防热及减阻设计具有重要意义。本文用有限差分法求解轴对称Ｎ－Ｓ方程模拟了球柱体头部反向喷流与超声速自由来流的干扰流场。研究了喷流出口压力对流场的影响。物面压力分布及喷流Ｍａｃｈ盘、弓形激波的脱体距离与实验值进行了比较，取得了一致的结果，喷流附近分离区的再附位置及再附产生的激波位置也与实验相符，但高压比下再附激波略强于实验。The counterflow nosejet in supersonic flow is an importantmeans for modifying the pressure or temperature distributions on forward facing surfaces,and for protecting the nose from ablation.The flowfield resulting from a sonic nosejet with various jet pressure issuing into a supersonic stream are studied numerically. The nosejet has a nozzle diam-eter equal to 0.132 cylinder diameter, and main stream has a Mach num-ber of 2.5.The pressure distributions along nose surface and the loca-tions of Mach disk and bow shock are compared with experiment data, good agreement is presented.Various flowfield features are discussed.

关 键 词：反向喷流 分离流动 数值模拟 飞机 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]