超声速流动中横向射流流场的影响参数  

Effecting parameters of supersonic flowfield with secondary injection

作　　者：孙得川[1] 蔡体敏[1] 

机构地区：[1]西北工业大学航天工程学院,陕西西安710072

出　　处：《推进技术》2001年第2期147-150,共4页Journal of Propulsion Technology

基　　金：国家重点实验室基金资助项目!(97JS6 0 3 2 ZS6 0 0 7)

摘　　要：采用高精度的WeightedENO格式 ,结合两方程湍流模型 ,准确模拟了二次射流形成的干扰流场 ,详细地描述了平板上单股射流干扰流场和喷管扩张段二次射流干扰流场中的激波、流动分离和旋涡运动 ,同实验结果进行了比较。探讨了射流 /主流总压比、射流宽度、以及射流与来流夹角对射流穿透深度、分离距离等影响 ,揭示了二次射流推力矢量控制干扰流场的控制机理。An explicit weighted essentially nonoscillatory discretization scheme (WENO) and two-equation turbulent model were used to calculate the supersonic flowfield over a two-demensional infinite flat with secondary injection. The flow structure including shock waves, flow separation, and vortexes was captured and compared with the experimental results. Some parameters affecting the supersonic flowfield, including the total pressure ratio of jet to freestream, slot width of injection, and the angle of injection were studied in more detail.

关 键 词：喷射控制 超音速射流 二次喷射 喷射混合流 状态参数 数值计算 横向射流流场 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程] V411