尾喷管构型对类乘波飞行器性能影响

Nozzle configuration effect on the performance of quasi-waverider

关键词:  类乘波飞行器+  尾喷管  升力  阻力  特性  俯仰力矩

Key words:  Quasi-waverider+  Tail nozzle  Lift  Drag  Characteristics  Pitching moment

摘要:

采用二维耦合隐式欧拉方程和标准k-ε湍流模型对类乘波飞行器内外流场进行了数值仿真研究,离散采用二阶迎风格式,在考虑粘性影响的前提下,分析了倾角为8,°11,°13°和15°的尾喷管对类乘波飞行器分别处于进气道关闭、发动机通流以及发动机点火三种不同的工作状态下性能的影响。结果表明当尾喷管倾角为11°时,飞行器的升力特性、阻力特性和俯仰力矩性能得到了权衡,性能得到了提高,为下一步的改进工作提供了参考。

Abstract:

Two-dimensional coupled implicit Euler equations and standard k-ε viscid models were introduced to simulate the flow of quasi-waverider,and the equations were discretized by the second order upwind.When the deflection angle of afterbody nozzle was 8°,11°,13° and 15°,respectively,the configuration of afterbody nozzle influencing the performance of quasi-waverider in three different working conditions including inlet closed,inlet open but unfired,inlet open and fired was discussed.Results show that when the deflection angle of afterbody nozzle is 11°,the lift force characteristic,the drag force characteristic and the pitching moment characteristic of the quasi-waverider are balanced,and the performance of the quasi-waverider is improved,which will can further guidance in the following design.