One Case of Shock-free Deceleration of a Supersonic Flow in a Constant Cross Section Area Channel

Dmitry E. Khazov

doi:10.14529/jsfi220402

Authors

Dmitry E. Khazov Institute of Mechanics, Lomonosov Moscow State University, Moscow, Russian Federation https://orcid.org/0000-0001-6950-5654

DOI:

https://doi.org/10.14529/jsfi220402

Keywords:

supersonic flow, permeable wall, Mach number, deceleration, injection/suction

Abstract

Air flows with supersonic speeds are used in many cases, for example, as aircraft air intakes, wind tunnels, and energy separation devices. In many cases it is necessary to decelerate the flow to sonic speeds. Traditionally the deceleration realized through the shocks system, which leads to total pressure losses. The article considers the method of deceleration of supersonic flows using permeable surfaces. In this case, the deceleration process occurs without shocks and, therefore, with lower total pressure losses. We have considered the flow in a tube with permeable wall located behind a supersonic nozzle. One-dimensional and axisymmetric mathematical models of such a device are developed. The calculation results are compared with experimental data. It is shown that, depending on the ratio of pressure inside the tube and the ambient pressure, different flow regimes inside the tube are possible: pure subsonic, transitional from supersonic to subsonic, and pure supersonic. The transition from supersonic to subsonic flow occurs without shocks due to the suction and friction combined effects.

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