Numerical study of control of normal shock by energy pulse

H. Yan, D. Knight, G. Elliott

Research output: Contribution to conferencePaper

Abstract

This paper presents a numerical study of controlling the normal shock in a Mach 1.5 flow by means of pulsed energy deposition. The purpose is to examine the capability of pulsed energy deposition to move a normal shock upstream in a mixed-compression inlet so as to counteract the effect of an expansion wave originating from the compressor face and moving the normal shock downstream. First, a two dimensional viscous simulation was performed to capture the normal shock formed in a Mach 1.5 nozzle. Then a 2D energy spot was instantaneously added half way through the cross section upstream of the normal shock. This energy spot was characterized by a Gaussian profile of temperature and pressure (density is assumed constant when the energy is deposited). The Mach 1.5 normal shock causes the separation of the boundary layer and the increase of the boundary layer thickness. Three different dimensionless energy levels (ε =1, 10 and 100) were considered. The interaction at ε = 100 demonstrated a prominent upstream movement of the normal shock, and a significant change of the separation region due to interaction of the energy spot induced compression wave with the separated boundary layer.

Original languageEnglish (US)
Pages14087-14096
Number of pages10
DOIs
StatePublished - Jan 1 2005
Event43rd AIAA Aerospace Sciences Meeting and Exhibit - Reno, NV, United States
Duration: Jan 10 2005Jan 13 2005

Other

Other43rd AIAA Aerospace Sciences Meeting and Exhibit
CountryUnited States
CityReno, NV
Period1/10/051/13/05

ASJC Scopus subject areas

  • Engineering(all)

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    Yan, H., Knight, D., & Elliott, G. (2005). Numerical study of control of normal shock by energy pulse. 14087-14096. Paper presented at 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, United States. https://doi.org/10.2514/6.2005-785