摘要
附面层引起的摩擦损失直接影响液体火箭发动机喷管效率,喷管附面层的计算对发动机性能的评估和提升具有重要意义。编制的用于计算液体火箭发动机喷管附面层的Fortran程序,对某型号发动机喷管的设计型面进行了计算,并讨论了附面层沿壁面的发展规律。结果表明:程序计算结果与CFD软件计算结果接近,对计算型面进行修正后比冲性能有所提升;在同样精度要求下,采用Fortran程序进行喷管附面层计算更方便,可显著缩短计算时间。
Friction loss caused by boundary layer directly affects the efficiency of liquid rocket nozzles.Calculation on nozzle boundary layer is of great meaning for the evaluation and improvement of the rocket engine performance.A FORTRAN program for liquid rocket engine nozzle boundary layer calculation is designed and applied to a specific nozzle contour.The regular pattern of the development of the boundary layer along the wall is discussed.The result of the program is close to the result calculated from CFD software,and specific impulse improvement is gained for the calculated nozzle by contour modification.Under the same precision,using the program will be more convenient and much more timesaving.
作者
刘鑫鹏
许晓勇
程圣清
Liu Xin-peng;Xu Xiao-yong;Cheng Sheng-qing(Beijing Aerospace Propulsion Institute,Beijing,100076)
出处
《导弹与航天运载技术》
CSCD
北大核心
2018年第2期55-60,共6页
Missiles and Space Vehicles
关键词
火箭发动机
附面层
喷管
型面
Rocket engine
Boundary layer
Nozzle
Contour
