摘要
对地面条件下大面积比喷管出现的分离流动进行了数值计算分析和试验。首先,利用商用CFD软件进行做数值计算,计算了多种工况,分析了燃烧室压强、喷管型面对分离流动的影响;然后,利用某型号固体火箭发动机进行喷管分离流试验,测得了喷管壁面上沿轴向的压强分布数据。试验捕捉到的与流场数值计算中得到的分离点位置相近,验证了流场数值计算的准确性,数值计算和试验为进一步深入研究打下基础。
The flow separation in the overexpanded nozzle on the ground was studied.First of all,commercial software of CFD was used to simulate the fluid field of overexpanded nozzle.Several flow simulation conditions were applied to study the factors of chamber pressure and nozzle contour,which might affect the flow separation.Then,the experiment of flow separation in the nozzle was done with a solid rocket motor,and the inside pressure data along the axis of the nozzle was gotten.The location of the separation point of simulation was similar to the experimental data,which proved the accuracy of the method of numerical simulation.The simulation and experiment provides the base for further study.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2010年第4期406-408,共3页
Journal of Solid Rocket Technology
关键词
固体火箭发动机
喷管
分离流动
数值模拟
试验
solid rocket motor
nozzle
flow separation
numerical simulation
experiment
