轴对称射流矢量喷管的试验和数值模拟

Numerical simulation of an axisymmetric fluidic vectoring nozzle

关键词:  可压缩流  矢量喷管+  射流  数值仿真

Key words:  Compressible flow  Vectoring thrust nozzle~+  Jet flow  Numerical simulation

摘要:

对基于激波来实现推力矢量的轴对称射流矢量喷管的缩比模型进行了测力和测压试验,用推广到可计算可压缩流的SIMPLE方法其内外流场进行了数值模拟,根据试验和数值模拟结果分析了喷管主流与次流相互作用产生的复杂流场结构、二次流流量和落压比对气动矢量角的影响,在落压比3～6范围内,二次流流量和喷管主流比值增大,气动矢量角增大,两者比值相同时,落压比增大,气动矢量角减小。

Abstract:

A sub-scale experimental static investigation for an axisymmetric fluidic vectoring nozzle was conducted. The force and wall pressure of the nozzle were measured in the experiment. The internal flow structure of the axisymmetric fluidic vectoring nozzle, induced by the interaction of primary inflow and secondary inflow, has been simulated with the SIMPLE method which is generalized to compressible-flow. The experimental and computational results show that flow flux of secondary flow injection and nozzle pressure ratio (NPR) influenced on the vectoring angle. While the NPR was 3～6, the ratio between injection flux and primary flow flux increase while the thrust vectoring nozzle increase. While the ratio between injection flux and primary flow flux is the same, the NPR increase, the thrust vectoring nozzle decrease.