摘要
利用了CFD软件对二维非对称喷管进行数值模拟,分析了不同内部喷管长度下,喷管压力、推力、升力和俯仰力矩的变化规律,以及对后体喷管性能的影响.提出了一种内部喷管长度选择方法,并采用这种方法所得的结论与NASA公布的模型进行比较,表明提出的方法具有可行性.
The CFD software is used to simulate the flow in the 2D asymmetric ramp nozzle. The change rule of pressure, thrust, lift and pitching moment of nozzle and the performance of the afterbody are analyzed under different internal portion length. A kind of method for choosing internal portion length of nozzle is brought forward. And the solution is compared to the model that NASA publicized. It is indicated that this method is feasible.
出处
《战术导弹技术》
北大核心
2007年第6期8-11,共4页
Tactical Missile Technology
关键词
后体喷管
膨胀波
高超声速
数值模拟
nozzle afterbody
expansion wave
hypersonic
numerical simulation
