Abstract
The problem of supersonic streamlining of an aerodynamic (AD) body, “a plate blunted by a cylinder”, by a flow with the freestream Mach number M = 4 containing an external energy source has been studied, taking into account physicochemical transformations. The results of the effect of the ratio of specific heats γ changing in the range from 1.1 to 1.4 on the dynamics of triple-shock configurations and vortex-contact structures are presented for the interaction of an energy source with the bow shock wave. The energy source is modeled via the heated rarefied layer (filament). The angles in the triple-shock configurations, the stagnation pressure, together with the frontal drag force, have been studied dependent on the specific heats ratio γ, the characteristics of the energy source, and also on the angle of the incident shock. Vortex-contact structures have been researched for the Mach numbers 7, 8, 9, as well as the generation of the Richtmyer-Meshkov instability accompanying the formation of a triple-shock configuration. The results show a strong influence of the specific heats ratio of the gas medium and the parameters of the energy source on the triple-shock configuration and aerodynamic characteristics of the body. This conclusion can be useful for aerospace applications in the area of the design of nozzles, intakes, and high speed flying vehicles. Additionally, the results show the possibility of flow control in the atmospheres of other planets using external energy deposition.
Highlights
Supersonic flow control using energy deposition in different places in the flow and on an AD body’s surface has been widely researched in modern aerospace engineering [1,2,3]
The effect of the external energy source in an oncoming flow in air was shown to lead to a decrease of the stagnation pressure, together with the drag force of the body
It has been stated that the triple-shock configurations accompanied by the vortex-contact structures were generated at the beginning stage of the process of energy release–shock layer interaction when the flow mode is close to the self-similar one [15,16,17]
Summary
Supersonic flow control using energy deposition in different places in the flow and on an AD body’s surface has been widely researched in modern aerospace engineering [1,2,3]. This paper is devoted to the problems of the influence of an external energy source on a shock layer initiated by supersonic streamlining the body, “a plate blunted by a cylinder”, under the Mach number of the oncoming flow M = 4 for gaseous media with the specific heats ratio γ in the range from 1.1 to. 9) modeling the vortex-contact structures accompanied the research of the dependence of stagnation pressure and drag force on γ and the rarefaction in the formation of triple-shock configurations, together with the generation factor of the the energy source hasinstability, been made. 8, 9) modeling the vortex-contact complex conservative difference schemes have enlarged conservationstructures propertiesaccompanied both inside the formation of triple-shock configurations, together with the generation of the Richtmyer-Meshkov the calculation area and near the boundaries of the streamlined body [30]. The results reflect the possibility of flow control in the atmospheres planets (characterized by γ different from 1.4) via the external energy deposition
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