Vortex distortion during vortex-surface interaction in a mach 3 stream

Iraj M. Kalkhoran

Research output: Contribution to journalArticle

Abstract

An experimental study has been conducted in a Mach 3 wind tunnel to investigate the behavior of supersonic vortices as they interact with a wedge surface placed in their passage. The experimental setup was arranged so that interactions resulted in a close encounter of the vortex core and the wedge leading edge. Spark shadow photographs of the flowfield along with pressure measurements on the wedge surface were used to study the interaction problem. In their most organized form, distortion of streamwise vortices upon interacting with the wedge was found to result in formation of symmetric detached shock fronts far upstream of the wedge leading edge followed by an apparent slip surface separating a subsonic region from a supersonic zone.

Original languageEnglish (US)
Pages (from-to)123-129
Number of pages7
JournalAIAA Journal
Volume32
Issue number1
StatePublished - Jan 1994

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Mach number
Vortex flow
Pressure measurement
Electric sparks
Wind tunnels

ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

Vortex distortion during vortex-surface interaction in a mach 3 stream. / Kalkhoran, Iraj M.

In: AIAA Journal, Vol. 32, No. 1, 01.1994, p. 123-129.

Research output: Contribution to journalArticle

Kalkhoran, Iraj M. / Vortex distortion during vortex-surface interaction in a mach 3 stream. In: AIAA Journal. 1994 ; Vol. 32, No. 1. pp. 123-129.
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