圆管内高超声速流的发展和激波形态的实验研究

An Experimental Investigation of Hypersonic Flow Development and Shock Pattern in a Circular Pipe

本文的研究目的是了解沿圆管内发展的高超声速流的结构。实验是在加拿大多伦多大学的高超声速炮风洞内完成的，风洞的自由射流马赫数Ｍ＿∞＝８．３０，总温Ｔ＿（ｔ∞）＝１０００Ｋ，总压Ｐ＿（ｔ∞）＝２６．５ＭＰａ单位雷诺数Ｒ＿ｅ＝３．２×ｌ０￣７。壁面静压以及内流中的若干截面内的皮托压力和静压测量结果揭示，管内产生的激波主要是斜激波形态，而且存在着较强的激波与边界层的相互干扰。实验发现，近管中心线的高超声速流动有不稳定现象；壁面的边界层，基本上是湍流边界层，特别是干扰区的下游；圆管出口的周向内壁面的顶壁面静压对管的攻角异常敏感。本文提供的结果，可以指导高超声速流的计算流体力学的方法和进展。

The present investigation is concerned with the understandingof the structure of the hypersonic flow development in a circular pipe.The experiments were conducted in the Hypersonic Gun Tunnel of UTIAS,Canada, at a free-jet Mach number of 8.30, unit Reynolds number of 3.2 ×10￣7/m,total temperature of 1000K and total pressure of 26.5MPa. Wallstatic pressure, as well as, in-stream pitot and static pressure measure-ments at several sections reveal that an oblique shock pattern is primarilyformed and there are stronger shock-boundary layer interaction in the pipe.It is found that the hypersonic flow near the centerline of pipe is somewhat unsteady and the boundary layer on the inner wall is basically tur-bulent, especially downstream of the interaction, and that the top wallstatic pressure in the pipe exit plane is very sensitive to the angle ofattack of the pipe. The present results may guide the development of compu-tational fluid dynamic codes applicable to hypersonic flows.