摘要
本文以Ｇｒｅｅｎ函数为基础的边界元法，结合时间历程法，计算机翼－尾翼组合体对突风动态响应的气动性能。本文介绍的方法，特别适于研究、分析各类飞行器非定常动态响应，为飞行器的设计及其非定常气动特性分析提供了一个行之有效的计算方法。编制的计算程序快捷、精度好。本文提供了单个机翼对突风动态响应的几个算例，有的与Ｌｏｍａｘ解进行了比较，吻合得很好，说明本文所使用的方法是可行的，程序是成功的。对于机翼－尾翼组合体的数值结果，则进一步提供了尾翼受机翼洗流影响的过程。
The boundary element method based on Green's law is presented in this paper for the computation of wing-tail combination's unsteady response to gust. lt supplies an effective and versatile tool for designing of vehicles and analyzing of their aerodynamic performances, particularly is suitable to numerical calculation for studying and analyzing of unsteady response process of various vehicles. Some results of single wing's unsteady response to gust are compared with Lomax theoritical solution from which it can be seen that coincidence between them is very well, and that this method is effective and versatile, the program is successful.The influence of wing wash process on the tail is also shown for wing-tail combinations.
出处
《空气动力学学报》
CSCD
北大核心
1996年第3期344-348,共5页
Acta Aerodynamica Sinica
关键词
超声速流
突风动态响应
机翼
尾翼
组合体
supersonic flow,unsteady response, numerical computation,wing-tail combination.
