摘要
采用SSTk ω湍流模型封闭轴对称粘性可压缩N S方程组,对双钟形喷管在不同环境压力下的流场进行数值模拟,并与相应的冷吹风试验结果进行对比验证。对比结果显示,数值模拟与冷吹风试验结果在流场结构及性能曲线上均吻合良好。这表明,该数值计算模型可有效应用于双钟形喷管的数值模拟及性能分析。计算和试验结果还显示:低空工况下,双钟形喷管在型面转折点处出现流动分离,喷管性能接近于小面积比基弧段喷管;高空工况则气流可完全附着于延伸段壁面,喷管总面积比得到有效应用。这一结果验证了双钟形喷管的高度补偿特性。
The numerical simulation and cold flow test for dualbell nozzle flow field at different ambient pressures are processed in this paper. In the simulation, the k ω turbulence model is selected to solve the controlled NS equations. The simulation results compared with the test results show that the numerical method in this paper is suitable for dualbell nozzle, to catch its complex flow charactesr including the shocks, the free shear layer and the large scale flow separation. The simulation and test results also show that controlled flow separation at sea level mode and full flow at high altitude mode can be observed as expected, so that the dualbell's altitude compensation is achieved.
出处
《导弹与航天运载技术》
北大核心
2005年第2期26-30,共5页
Missiles and Space Vehicles
基金
国家 863-2资助项目(2002AA722020)
