2021/05/08 by Pradeepa T. Karnick, Karnick, Pradeepa T., Kartik Venkatraman +1
Engineering · #Computational Fluid Dynamics and Aerodynamics #FOS: Physical sciences #Fluid Dynamics (physics.flu-dyn) #Fluid Dynamics and Turbulent Flows #Plasma and Flow Control in Aerodynamics
paper · pdf · doi:10.48550/arxiv.2105.03724
openalex publication_date 2021/05/08 · openalex created_date 2025/10/10 · openalex updated_date 2026/07/28
We numerically examine the mechanisms that describe the shock-boundary layer\ninteractions in transonic flow past an oscillating wing section. At moderate\nand high angles of incidence but low amplitudes of oscillation, shock induced\nflow separation or shock-stall is observed accompanied by shock reversal. Even\nthough the power input to the airfoil by the viscous forces is three orders of\nmagnitude lower than that due to the pressure forces on the airfoil, the\nboundary layer manipulates the shock location and shock motion and\nredistributes the power input to the airfoil by the pressure forces. The shock\nmotion is reversed relative to that in an inviscid flow as the boundary layer\ncannot sustain an adverse pressure gradient posed by the shock, causing the\nshock to move upstream leading to an early separation. The shock motion shows a\nphase difference with reference to the airfoil motion and is a function of the\nfrequency of the oscillation. At low angles of incidence, and low amplitudes of\noscillation, the boundary layer changes the profile presented to the external\nflow, leads to a slower expansion of the flow resulting in an early shock, and\na diffused shock-foot caused by the boundary layer.\n