平面运动激波在定常超音速劈表面马赫反射的研究

INVESTIGATION OF MACH REFLECTION FOR A PLANAR MOVING SHOCK PROPAGATING INTO STEADY SUPERSONIC FLOW FIELD AROUND WEDGE

本文介绍了在电控双驱动激波风洞中进行的平面运动激波在有定常超音速绕流的尖劈表面马赫反射的实验。这种反射现象属于准定常的,在实验中观察到了四种反射(RR,SMR,CMR和DMR)。本文还计算了三波点Τ的迹线及弯折点Κ的迹线分别和劈面的夹角χ和χ',以及各种反射相互转变的边界。发现运动激波波前定常超音速气流马赫数Μ_0会影响χ和χ'角,使(θ_ω+χ,Μ_s)平面上各种反射的转变边界发生变化,但不影响(θ_w,Μ_s)平面上的各条转变边界线。

The experiment of Mach reflection for a planar moving shock propagating into a steady supersonic flow field around a wedge was conducted in a double driver shock tunnel. The reflection phenomenon is pseudo-stationary. Reflections of four different types (RR, SMR, CMR and DMR) were observed in the experiment. The angles X and X＇of the first-triple-point T and the kink K, and the transition boundaries between various reflections were calculated. It is found that the angles X and X＇and the transition boundaries in the (θ_w+X, M_s) plane depended on the steady supersonic flow Mach number M_0 ahead of the moving shock, whereas the boundaries in the (θ_w, M_s) plane do not.