一种快速评定进气道/发动机稳态匹配工作点及稳定裕度的方法

 一、引言 无论在飞机的研制还是在原型机的试飞中,都要求能迅速确定在飞行包线内任意一点上进气道/发动机的稳态匹配工作点。但是由于进气道时性本身的多变性,即它不仅随进气道几何形状,而且还随飞行Ma数、迎角。和侧滑角卢而变;而风洞试验却只能在上述变量的有限组合下进行。因此,对一个

A METHOD FOR FAST ESTIMATION OF STEADY INLET/ENGINE MATCHING STATE AND STABILITY MARGIN

It is certainly desirable to know steady inlet/engine matching state at any point of flight envelope either for development or for flight test of a new plane. But this task is complexed because of the uncertainty of inlet characteristics itself, i.e, it is not only a function of inlet geometry, but of flight Mach number, angle of attack, slip angle and of the fact that inlet wind tunne test can only be performed at limited combinations of the variables above. A method for rapid estimation of inlet/engine steady matching state and stability margin is presented in this paper, which is based on the concepts of subcriti-cal level （or Buzz margin and supercritical level or "ithing" oscilation margin） and generalized inlet characteristics, Practice has shown its availability.