A computational study of laminar/turbulent and subsonic/supersonic horseshoe vortex systems generated by a cylindrical protuberance mounted on a flat plate is presented. Various vortex structures have been predicted and are discussed. For a low subsonic laminar flow, the number of vortex arrays increases with Reynolds number (with fixed incoming boundary layer thickness), in agreement with both experimental and numerical observations. The relationships among pressure extrema, vorticity and the singular points in the flow structure on the plane of symmetry over the flat plate are studied. Mach number effects have also been investigated for laminar flow at one Reynolds number. The outermost singular point moves upstream when free-stream Mach number increases. The size of the whole vortex structure increases dramatically due to shock wave/boundary-layer interaction. The computed laminar horseshoe vortex systems start from a saddle point of attachment. In the case of a supersonic turbulent flow at a high Reynolds number, the computed results predict the same features of this complex juncture flow as those indicated by the experimental results, such as the upstream shock-wave/boundary-layer interaction and the classical horseshoe vortex system starting from a saddle point of separation. The calculations provide details of the downstream wake/shock-wave interaction and the near wake tornado-like vortex structure. The overall flow topology is discussed.
|State||Published - 1 Jan 1991|
|Event||AIAA 22nd Fluid Dynamics, Plasma Dynamics and Lasers Conference, 1991 - Honolulu, United States|
Duration: 24 Jun 1991 → 26 Jun 1991
|Conference||AIAA 22nd Fluid Dynamics, Plasma Dynamics and Lasers Conference, 1991|
|Period||24/06/91 → 26/06/91|