结冰飞机气动系数和气动导数的估算方法  

The Estimation of Aerodynamic Coefficients and Derivatives for an Icing Aircraft

作　　者：杜亮[1] 洪冠新[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《航空计算技术》2004年第3期16-19,共4页Aeronautical Computing Technique

摘　　要：飞机在结冰后气动系数、导数会发生变化,由于多种原因,精确地计算其变化量是很困难的。为定量计算其对飞机性能、品质的影响并有效地控制飞机,本文从工程的需要出发,给出一种估算结冰飞机气动系数、导数的方法,对线性变化的各个气动导数、非线性变化的最大升力系数和阻力系数进行估算。根据估算结果与实验数据的比较表明该方法实用有效。Aerodynamic coefficients and derivatives are influenced after icing, for many reasons, it is very difficult to calculate their changes accurately. To calculate the change of performance, quality of airplane and control the airplane effectively, the estimation of airplane's aerodynamic coefficients and derivatives were established for the needs of engineering, the estimation includes the linear aerodynamic derivatives, nonlinear maximum lift coefficient and drag coefficient. The comparison between calculations and experiments shows that the estimation is practical and effective, it can be a reference of person who major in airplane icing.

关 键 词：飞机 结冰 气动系数 飞行力学 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程]