【摘要】 <正> 为改善飞机的起降性能,在设计,选择各种增升装置过程中,必须进行多段冀型的低速风洞实验。 通常二元实验段的高宽比相当大,而模型几何展弦比小,实验段侧壁附面层将影响实验结果。模型越窄,影响就越严重。洞壁的湍流附面层在一个楔形区内向模型前缘的层流区扩展,使模型中部剖面转捩区大大前移。当二元翼型实验存在压力梯度时,洞壁处的流动变得异常复杂,总强度等于翼型环量的旋涡分散在洞壁的各个方向上,在翼型的各个截面产生相应的诱导速度和诱导迎角,从而影响了流动的二元性。更多还原

【Abstract】 The present paper describes some research results of boundary layer control on the wall of a two dimensional low speed wind tunnel with blow-ing system. In the experimental research the airfoil models with single and double slotted trailing edge flap were adopted. The boundary layer control is a very effective method to prevent the premature flow sepa-ration in the junction corner between the tunnel wall and the airfoil model and to get rid of three dimensional effect for single or multi-component airfoil research.In the paper, some of contrast research results are given by figures and the selection of blowing quantity and the disposition of the blowing slots are described.更多还原