Journal d'ingénierie aéronautique et aérospatiale
Libre accès
ISSN: 2168-9792
ISSN: 2168-9792
Ahmad Sedaghat*,Mohammad Amin Aghahosaini
Interaction of a supersonic vortex with an oblique shock wave is an important phenomenon because of strong acoustic levels and its adverse effect in aerodynamic performance in high speed flows. In this paper, a mathematical model for the vortex is introduced which predicts experimentally generated vortices accurately. Then, the shock wave-vortex interaction was numerically studied using a finite-volume TVD scheme for solving Euler equations. From the results, two interaction regimes are recognized, namely weak and strong regimes. It is shown that vortex breakdown is possible in the case of strong interaction which can significantly alter aerodynamic characteristics of flyers or acoustic field. Results for two case studies are presented here with the freestream Mach numbers of 2.5 and 2.9. The effects of different parameters in vortex breakdown are investigated. It is found that the smaller vortex core sizes with higher intensity may result in stronger interaction at higher Mach numbers leading to vortex breakdown.