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以高速风洞气动力测量为研究手段,开展了弹舱开启对飞翼布局飞机气动特性影响及其流动控制试验研究。试验结果表明,对于飞翼布局飞机,弹舱开启主要影响飞机阻力特性,巡航状态下,弹舱开启后使得全机阻力增加60%～110%,Ma=0.8时全机升阻比降低34%。通过在弹舱前缘安装扰流片,对弹舱腔口剪切层施加流动控制,巡航状态下弹舱开启附加阻力最多降低20%,Ma=0.8时全机升阻比提高12.6%。
Taking the aerodynamic measurement of high-speed wind tunnel as the research method, the influence of the opening of the bomb bay on the aerodynamic characteristics of the aircraft with the flying wing and the experimental study of its flow control are studied. The test results show that for the flying wing layout aircraft, the opening of the cabin mainly affects the resistance of the aircraft. In the cruising state, the resistance of the whole machine is increased by 60% ~ 110% when the cabin is opened, and the drag-and-drop ratio of the whole machine is reduced by 34% when Ma = . By installing the spoiler on the leading edge of the cargo tank, flow control is applied to the shear layer of the cascade. The additional opening resistance of the cargo tank under cruising condition is reduced by 20% at most, and the lift-drag ratio is increased by 12.6% when Ma = 0.8.