摘要
基于工程快速计算方法研究了高超声速高升阻比飞行器过渡流区气动特性.首先应用一与所研究飞行器相近气动布局作为验证外形,对连续流区牛顿类高超声速工程快速计算方法在高超声速高升阻比飞行器上的计算精度进行了评估.研究表明,高超声速工程快速计算方法在其应用范围内,对高超声速高升阻飞行器的气动特性具有较高的预测精度,可以满足工程设计需要.最后,在连续流区使用同样的计算方法,同时考虑高空稀薄气体效应,通过所建立的桥函数给出了所研究高超声速高升阻比飞行器过渡流区的气动特性.
Aerodynamics characteristics of hypersonic high lift-drag ratio vehicle based on engineer rapid prediction method had been given in transition zone.The precision of Newton＇s theory in continual flow zone was validated on hypersonic high lift-drag ratio vehicles with a configuration that is similar to the studied one.The result showed that hypersonic engineer rapid prediction method has a very good precision on the areodynamics characteristics of hypersonic high lift-drag ratio vehicle in a rang of attack angle,side angle and rudder angle.the request of engineer design can be completely satisfied.Finally,the aerodynamics charactoristics of hypersonic high lift-drag ratio vehicle was presented by the bridge function at the condition of applying the same method in continual flow zone and considering rare gas effect.
出处
《战术导弹技术》
2011年第1期37-43,共7页
Tactical Missile Technology
基金
国家自然科学基金项目(60736023)
关键词
高超声速
工程快速计算方法
过渡流区
气动特性
hypersonic
engineer rapid calculation method
transition zone
aerodynamic characteristics
