Effects of micro-vortex generators on shock wave structure in a low aspect ratio duct, numerical investigation

摘要

The interaction between the shock wave and boundary layer and its induced separation is an undesirable phenomenon in the design of supersonic systems. The control of this phenomenon by active and passive methods is highly important in the design of aerodynamic systems. In the present work, different series of micro vortex generators were investigated as a passive control method (with the ability to increase the flow momentum), affecting the structure of a compressible flow at the Mach number of 2.05 in a low-aspect-ratio duct. In this regard, the finite volume method was used in the Open-Foam package. The obtained results were first validated against experimental data, and then four different vortex generators with a height of 10 mu m were investigated. The results revealed that the use of vortex generators caused a reduction in the shock wave strength and energy loss across the flow. Furthermore, applying a vortex micro-generator with the outer body of national advisory committee for aeronautics 4412 airfoil led to a significant decrease in the strength of shock waves. Also, a vortex generator could shift the shock wave occurrence location to the downstream.