近耦鸭式布局干扰气动力实验研究

EXPERIMENTAL INVESTIGATION OF THE INTERFERENCE AERODYNAMICS OF CLOSE-COUPLED CANARD CONFIGURATION

使用能单独测量鸭翼部分气动力的“鸭翼天平”及全机气动力天平,对一可组拆的鸭式布局模型进行了干扰气动力的实验研究。发现在α<20°时鸭翼与主翼间的干扰是不利的,使升力下降。α>32°时干扰变得有利。α=32°时干扰升力可占到总升力的24％。若主翼为前掠翼,构成鸭式布局的气动特性更好。

A method to investigate the aerodynamic interferences (between the canard and the wing using a combined model is described. The method can provide a clear picture to the interferences. A typical interference characteristics for the life of a canard configuration with sweep-back wing is presented. At small angle of attack, the interferences are pernicious. However, as the angle of attack increases, the interferences turn increasingly beneficial. When α = 20°, the lifting interference is null, and for α = 32°, it rises to 24% of the total lift. Moreover, the stall is put-off by an angle greater than 8 degrees. A preliminary discussion on the mechanism of the interferences is also given. The interference aerodynamic characteristics of a canard configuration with a swept-forward wing are briefly introduced too. The swept-forward wing with canard would earn more favorable results than the swept-back wing canard configuration does from the aerodynamic interference.