亚、超音速机翼非定常广义气动力系数之间的关系

 <正> 研究弹性飞机的动力学特性应计及非定常广义气动力。为了尽可能保留非定常运动历程,应首先计算由阶跃函数形式下洗产生的非定常气动力函数(指示函数或指数函数),再利用卷积形式的迭加原理处理任意函数形式下洗产生的非定常气动力。用振型法建立飞机弹性运动方程,可将飞机上任一质点的弹性位移近似地表示为

THE RELATION AMONG THE GENERAL UNSTEADY AERODYNAMIC COEFFICIENTS OF A WING IN SUBSONIC AND SUPERSONIC SPEED

The approximate dominant pole values of the linearized aerodynamic system(such as a wing with airflow can be obtained only with the concept of "equivalent system" and an indicial function f (t) of . general unsteady " aerodynamic obtained by numerical method, if flight Mach number (subsonic and supersonic speed) and the parameters of the wing are given. According to the principle of the indicial function, it can be considered that there are two dominant poles for the linearized aerodynamic system. So that the rest of indicial functions of the wing ftek ( t ) (k=j) are able to be obtained by its corresponding value at t =0, t = ts. This simplifies the calculation of the unsteady aerodynamic coefficient of the wing and reduces the order of the eigenfunctiou of the dynamic system