Transonic buffet in the finite span Benchmark Supercritical Wing (BSCW)

Transonic buffet is caused by shock oscillations that are triggered by shock induced boundary layer separation. We study this phenomenon in the context of the Benchmark Supercritical Wing (BSCW) at a Mach number of 0.85 and a chord based Reynolds number of 4.491 million. The aspect ratio of the wing is 2. The flow over the wing is shown to have a significant span-wise component giving rise to span-wise wing-tip to root flow that shows a distinctive travelling wave behavior. However, the shock buffet motion estimated at two span-wise stations, namely 10% and 60% span show the same frequency and amplitude despite flow separation being significantly strong closer to the root.