弹舱对飞翼布局飞机气动特性影响及其控制  

Study on the effect of weapons bay on aerodynamic characteristics of flying wing aircraft and its control

作　　者：冯强[1] 张洋[1] 崔晓春[1] 

机构地区：[1]中国航空工业空气动力研究院高速高雷诺数航空科技重点试验室,沈阳110034

出　　处：《实验流体力学》2013年第3期31-34,40,共5页Journal of Experiments in Fluid Mechanics

基　　金：航空科学基金项目(20111226003;20111526007)

摘　　要：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%。An experiment was conducted to investigate aerodynamic characteristics of flying wing aircraft with opened weapons bay by means of force and moment measurements. The results indicate that, for flying wing configuration aircraft, the increment of total vehicle drag was as much as 60%-110% when the weapons bay doors opened, and lift drag ratio reduced by 34% at Ma = 0.8. Conventional leading edge spoilers were used to disturb free shear layer of the weapons bay. Using the flow control method, additional drag of weapons bay can be reduced by 20% at most, and the lift-drag ratio increased by 12.6% at Ma =0. 8.

关 键 词：飞翼布局 弹舱 流动控制 风洞试验 减阻 

分 类 号：V211.46[航空宇航科学与技术—航空宇航推进理论与工程]