飞机平尾偏转对大迎角动态气动特性的影响

 给出了 BJ-1背景机有不同平尾偏角时静态和大振幅俯仰振荡情况下的气动特性。根据风洞实验结果,采用基于三角剖分数据库建模的方法,计算了任意平尾偏角和任意振动频率时的背景机动态气动特性,与实验结果比较表明,提出的有平尾偏角的建模方法能提供任意舵偏时的全机气动特性。在非定常建模的基础上,采用动导数仿真,分析了不同平尾偏角时的动导数,结果表明,水平尾翼偏角主要对零动态阻尼所对应迎角有较大影响,随着舵偏角的增大,该迎角减小。

EFFECTS OF TAILPLANE TURN ON THE UNSTEADY AERODYNAMIC OF THE AIRCRAFT PITCHING IN VERY LARGE AMPLITUDE

The steady and unsteady wind tunnel test was carried out about BJ 1 aircraft and the aerodynamic characteristic was analyzed. According to the results of the tests, the unsteady aerodynamic was calculated at arbitrary angles of the tailplane and pitching frequency using the method of a data base model. On the basis of the mathematical model, the dynamic derivative of the aircraft at the different angles of the tailplane was analyzed using the technique of dynamic derivative simulation. It showed that the angle of the tailplane affected the angles of attack corresponding to the zero damping severely.