分离流动对矢量喷管性能的影响  

Effects of flow separation on the performance of thrust-vectoring nozzle

作　　者：马会民[1] 樊思齐[1] 卢燕[1] 

机构地区：[1]西北工业大学航空动力与热力工程系,陕西西安710072

出　　处：《推进技术》2003年第5期421-424,共4页Journal of Propulsion Technology

摘　　要：采用有限体积法计算了轴对称矢量喷管三维粘性流场,通过改进人工粘性及其边界条件提高了计算的收敛性和数值模拟的精度。利用数值模拟研究了矢量喷管的分离流动对矢量推进性能的影响,通过同实验结果对比,验证了数值模拟的精度。研究表明,分离流动对矢量喷管的性能参数尤其是有效矢量角具有较大影响。Finite Volume Method (FVM) was used to calculate the 3-D viscous flow in the vectoring exhaust nozzle. The artificial dissipation and its boundary condition were improved to quicken the convergence and upgrade the precision of the numerical simulation. The effects of the flow separation in axisymmetric thrust-vectoring nozzle on performance of the thrust-vectoring propulsion were investigated . The comparison between the computation and experimental data validates the precision of the numerical simulation. The results show that the flow separation has much effect on the performance parameters, especially the efficient deficient angle of the nozzle.

关 键 词：矢量喷管 分离流 有限体积法 纳维尔-斯托克斯方程 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]