二次流喷口形状对激波矢量控制喷管推力矢量特性影响

基于CFD数值模拟技术，考虑变比热比及温度对黏度的影响，针对二次流喷口主要几何参数（二次喷射角度及喷口无量纲展向长度）在不同喷管落压比、二次流压比工况下对激波矢量控制喷管三维流动特性及推力矢量特性进行分析.研究表明：喷射角度增加，二次流喷射前主分离线前移，激波角度增加，在较小的二次流压比下随着喷射角度增加，推力矢量角增大，二次流压比为1.0和1.2时，存在最佳的喷射角度使得推力矢量角最大；喷口无量纲展向长度小于1.0时，喷口前分离涡演变为马蹄涡，并在喷口下游诱导尾涡，二次流压比大于0.6时随喷口无量纲展向长度增大，推力矢量角度增加.

Effects of secondary injection forms on thrust vector performance of shock vector controlling nozzle

By taking alterable specific heat ratio and effects of temperature on viscosity coefficient into account,based on CFD technology,effects of secondary injection geometric parameters,including injection angle and non-dimension slot width,on three dimensional flow characteristic and vector performance of shock vector controlling nozzle under different nozzle pressure ratios and secondary pressure ratios were investigated.Results show that,with increase of injection angle,position of main separation line before injection slot moves forward and shock angle ascends.In case of smaller secondary pressure ratio,thrust vector angle increases with the injection angle.When secondary pressure ratios equal to 1.0 and 1.2,there is an optimal injection angle for a maximal thrust vector angle.If non-dimension slot length is less than 1.0,the separation vortex before injection slot becomes into horse vortex and induces wake vortex.When secondary pressure ratio is larger than 0.6,thrust vectoring angle ascends with the increase of non-dimensional slot length.