Bio-Inspired Applications in the Reduction of Shock-Induced Boundary Layer Separation

Boundary layer separation presents significant challenges in supersonic flow regimes, adversely affecting aerodynamic performance and stability through increased turbulence and drag. Turbulence and drag are prevalent due to separation caused by compression and expansion phenomena that are common at such speeds. Interest in supersonic flow control has increased for development of next generation aircraft, using passive and active methods to reattach the boundary layer and delay turbulent separation. This study explores the application of bio-inspired passive flow control techniques using shark skin-inspired surfaces to mitigate the effects of shock-induced boundary layer separation in supersonic flow. Separation bubble size on three biomimetic surface samples in two shock-impingement arrangements was compared to the no shock and uncoated cases. Preliminary results indicate a significant reduction in the separation bubble size when utilizing these bio-inspired surfaces, demonstrating their potential for improving aerodynamic efficiency in high-speed flows. The findings suggest that such passive flow control methods can be instrumental in advancing supersonic vehicle design, offering a sustainable and effective solution for managing boundary layer separation.