The effect of shock strength on oblique shock wave-vortex interaction

Michael K. Smart, Iraj M. Kalkhoran

Research output: Contribution to conferencePaperpeer-review

Abstract

An experimental study of the interaction between streamwise vortices and two-dimensional oblique shock waves has been conducted at Mach 2.5. The experiments involved positioning an instrumented two-dimensional wedge downstream of a semi-span wing so that the trailing tip vortex from the wing interacted with the oblique shock wave formed over the wedge surface. The experiments were designed to simulate interaction of streamwise vortices with shock waves formed over aerodynamic surfaces or in supersonic inlets. The influence of oblique shock wave intensity on this inherently three-dimensional interaction was examined for vortices of variable strength. Results indicated that the interaction of a moderate strength vortex with an oblique shock wave can lead to the formation of a steady separated shock structure upstream of the oblique shock front. The scale of the structure increased with shock wave intensity and showed a close resemblance to the unsteady vortex distortion observed during the head-on interaction of streamwise vortices with a wedge leading edge reported in previous studies. In some instances the separated shock structure was observed to continue through the oblique shock front to strike the shock generating wedge forming a three-dimensional shock wave-boundary layer interaction.

Original languageEnglish (US)
StatePublished - 1995
Event33rd Aerospace Sciences Meeting and Exhibit, 1995 - Reno, United States
Duration: Jan 9 1995Jan 12 1995

Other

Other33rd Aerospace Sciences Meeting and Exhibit, 1995
CountryUnited States
CityReno
Period1/9/951/12/95

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

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