论文部分内容阅读
1.引言 高超声速机动飞行器(如航天飞机、机动导弹等)的气动控制翼,为了转动灵活,在弹体和控制翼之间总有一定宽度的缝隙。出于翼前物面压力一般总是大于翼背风面的压力,因而形成了缝隙内流。这样,外物面边界层内的热气体流入缝隙内,产生了缝隙流气动加热及缝隙的热防护等问题。当翼转角足够大时,还会引起翼前物面边界层的分离再附,这对缝内流动有很大影响;而缝隙流反过来也会影响分离再附区的流动性质和整个弹体的气动力特性。控制翼引起的激波与湍流边界层相互干扰,本来就是很复杂的
1. INTRODUCTION The aerodynamic control wing of a hypersonic maneuverable vehicle (such as a space shuttle, a maneuvering missile, etc.) has a certain width of clearance between the projectile and the control wing for rotational flexibility. The pressure on the front surface of the wing is always greater than the pressure on the wing leeward, thus creating a gap flow. In this way, the hot gas in the boundary layer of the outer surface flows into the gap, resulting in problems of aerodynamic heating of the gap flow and thermal protection of the gap. When the wing angle is large enough, it will also cause separation and re-attachment of the boundary layer of the anterior wing plane, which has a great influence on the flow in the seam. The slit flow in turn will affect the flow properties of the separation and reattachment zone and the entire projectile Aerodynamic characteristics. The shock wave caused by the control wing interacts with the turbulent boundary layer and is inherently complicated