Effect Of Micro Vortex Generators in Improving Shock Wave Boundary Layer Control

Micro-vortex generators (MVGs) are effective in passively controlling flow separation due to shock wave boundary-layer interactions in high-speed aerodynamics. MVGs not only minimize separation but also decrease boundary layer displacement thickness compared to traditional vortex generators.



Optimized MVG design has not been established for supersonic and transonic airfoils, and shock wave strength reduction was not the primary focus of the research studies. The primary goal of this research is to reduce the shock induced boundary layer separation and shock wave strength reduction. The results are analyzed through shadowgraph technique and pressure transducers.



A modified Split-Hopkinson Pressure Bar actuated by a high-speed servo valve is used to generate shock waves. The airfoil tested will have a chord length of 10 cm, and the overall height of the micro vortex generators will range between 10-100% of the boundary layer height. The number of MVGs and the placement of them will be optimized during experimental testing. Detailed investigation into the interaction between MVG-generated vortices and the shock foot will be the secondary goal.