Abstract
In this paper, we study the intersection (interaction) between several steady shocks traveling in the same direction. The interaction between overtaking shocks may be regular or irregular. In the case of regular reflection, the intersection of overtaking shocks leads to the formation of a resulting shock, contact discontinuity, and some reflected discontinuities. The type of discontinuity depends on the parameters of incoming shocks. At the irregular reflection, a Mach shock forms between incoming overtaking shocks. Reflected discontinuities come from the points of intersection of the Mach stem with the incoming shocks. We also consider the possible types of shockwave configurations that form both at regular and irregular interactions of several overtaking shocks. The regions of existence of overtaking shock waves with different types of reflected shock and the intensity of reflected shocks are defined. The results obtained in the study can potentially be useful for designing supersonic intakes and advanced jet engines.
Highlights
In a stationary supersonic flow, two types of shock wave reflection are distinguished— regular and Mach reflection [1]
Flow turns in counter-clockwise direction are shown in Figure 1a, where M is the Mach number, T is the point of intersection of the shock waves, R is the reflected discontinuity, σ1 and σ2 are the overtaking shock waves, σ3 is the main shock, τ is the tangential discontinuity, ← is the left discontinuity, and→ is the right discontinuity
The interference of shock waves that deflect the flow in one direction is considered
Summary
In a stationary supersonic flow, two types of shock wave reflection are distinguished— regular (two-wave configuration) and Mach reflection (three-wave configuration) [1]. Ashock wave structure composed of overtaking shocks of the same intensity is of the lowest level in terms of total pressure loss [10] Such a shock wave structure is optimal for supersonic air intake. Various criteria for the optimization of a shock wave structure, composed of overtaking shocks, were formulated [14,15] This theory was presented in relation to the external aerodynamics of supersonic aircraft in [16]. Solutions to the problems of shock wave structures on the plane of a shock polar, the determination of the domains of existence, the intensity of a reflected discontinuity, and the use of shock wave structures in external compression air intake are all considered in the study. It is convenient that the polar begins at the origin of coordinates [0,0]; it is usually constructed in the variables (lnJ, β)
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