论文部分内容阅读
采用高超声速风洞测力试验方法测量钝头飞行器头部减阻杆的高超声速气动特性,研究减阻杆的气动减阻原理,分析了多组不同构型减阻杆的减阻效果。结果表明,减阻杆显著减少了钝头飞行器高超声速的阻力,最大的减阻率达到60%之多;减阻效果与减阻杆构型和迎角状态密切相关;减阻杆会诱发稳定性、“热斑”以及非定常脉动等不利问题。
The hypersonic aerodynamic characteristics of the drag reducer on the head of blunt-hovercraft were measured by using hypersonic wind tunnel force test method. The aerodynamic drag reduction principle of the drag reducer was studied. The drag reduction effect of the drag reducer with different configurations was analyzed. The results show that the drag reduction rod significantly reduces the hypersonic drag of the blunt-nose vehicle, and the maximum drag reduction rate reaches as much as 60%. The drag reduction effect is closely related to the configuration of the drag reduction rod and the angle of attack. The drag reduction rod induces the stability Sexual, “hot spot ” and other unfavorable problems such as unsteady pulsation.