TY - CONF
T1 - Planar laser sheet visualization of oblique shock wave/vortex interaction
AU - Kalkhoran, Iraj M.
AU - Smart, Michael K.
N1 - Funding Information:
This work was supported by the Air Force Office of Scientific Research under Grant F49620-94-1-0210. The assistance provided by Lester Orlick and Sevetozar Popovic was greatly appreciated during the experimental study.
Publisher Copyright:
© 1996 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 1996
Y1 - 1996
N2 - Planar laser sheet visualizations of the flowfield generated by the interaction of a streamwise wing tip vortex and a strong oblique shock front at several distances downstream of a shock generating wedge were performed in a Mach 2.49 flow. The experimental scheme involved positioning a two-dimensional wedge surface downstream of a vortex generator wing section so that the wing-tip vortex interacts with the planar oblique shock front. The results of the investigation revealed an expansion of the vortex core in crossing a strong oblique shock front. The maximum vortex core diameter was seen to occur at a distance of 12.7 mm downstream of the wedge leading edge while at distances further downstream, the vortex core diameter remained approximately constant. The vortical structure was observed to persist along the entire chord of the shock generating wedge but was seen to diffuse with distances downstream of the wedge leading edge. Measurements of the vortex position relative to the wedge surface indicated that immediately downstream of the normal portion of a bulged-forward shock wave, the vortex axis was parallel to the direction of the freestream flow. On the other hand, the vortex was observed to travel parallel to the wedge surface at distances downstream of the wedge mid-chord position. The conical structure which forms as a result of vortex distortion was found to be sensitive to downstream disturbances in a manner similar to the incompressible vortex breakdown.
AB - Planar laser sheet visualizations of the flowfield generated by the interaction of a streamwise wing tip vortex and a strong oblique shock front at several distances downstream of a shock generating wedge were performed in a Mach 2.49 flow. The experimental scheme involved positioning a two-dimensional wedge surface downstream of a vortex generator wing section so that the wing-tip vortex interacts with the planar oblique shock front. The results of the investigation revealed an expansion of the vortex core in crossing a strong oblique shock front. The maximum vortex core diameter was seen to occur at a distance of 12.7 mm downstream of the wedge leading edge while at distances further downstream, the vortex core diameter remained approximately constant. The vortical structure was observed to persist along the entire chord of the shock generating wedge but was seen to diffuse with distances downstream of the wedge leading edge. Measurements of the vortex position relative to the wedge surface indicated that immediately downstream of the normal portion of a bulged-forward shock wave, the vortex axis was parallel to the direction of the freestream flow. On the other hand, the vortex was observed to travel parallel to the wedge surface at distances downstream of the wedge mid-chord position. The conical structure which forms as a result of vortex distortion was found to be sensitive to downstream disturbances in a manner similar to the incompressible vortex breakdown.
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M3 - Paper
AN - SCOPUS:84962159960
T2 - 34th Aerospace Sciences Meeting and Exhibit, 1996
Y2 - 15 January 1996 through 18 January 1996
ER -