TY - CONF
T1 - The effect of shock strength on oblique shock wave-vortex interaction
AU - Smart, Michael K.
AU - Kalkhoran, Iraj M.
N1 - Funding Information:
This work was supported by the Air Force Office of Scientific Research under Grant F49620-93-1-0009 and by NASA Lewis Research Ccnter under Grant NAG3-1378. The assistance of Mr Lester Orlick and Mr Frank Wang was greatly appreciated during the work.
Funding Information:
This work was supported by the Air Force Office of Scientific Research under Grant F4%20-93-1-0009 and by NASA Lewis Research Ccnter under Grant NAG3-1.178. The assistance of Mr Lester Orlick and Mr Frank Wang was greatly appreciated during the work.
Publisher Copyright:
© 1995 by the American Institute of Aeronautics and Astronautics, Inc. All right reserved.
PY - 1995
Y1 - 1995
N2 - 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.
AB - 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.
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M3 - Paper
AN - SCOPUS:84963516437
T2 - 33rd Aerospace Sciences Meeting and Exhibit, 1995
Y2 - 9 January 1995 through 12 January 1995
ER -