Transition Effect on Shock Wave / Boundary Layer Interaction at M=1.47

Shock-induced heating and transition to turbulence in a hypersonic boundary layer

“…The basic triple-deck theory of weak shock waves interacting with laminar boundary layers was formulated first by Lighthill (1950), who quantified the upstream extent of the pressure disturbance on the wall surface. More recently, several efforts in characterizing shock waves interacting with transitional boundary layers have been undertaken (Vanstone et al 2013;Sandham et al 2014;Schülein 2014;Davidson & Babinsky 2015;Polivanov, Sidorenko & Maslov 2015;Willems, Gülhan & Steelant 2015;Lash et al 2016;Currao et al 2020). A recent review paper by Knight & Mortazavi (2017) summarizes important studies in this area.…”

Effective plasma buffet and drag control for laminar transonic aerofoil

“…In Polivanov et al, 5 it was found that the minimum size of the zone of SWBLI and low level of pulsations may be achieved if the state of inflow boundary layer corresponds to the beginning of the laminar-turbulent transition (low level of intermittency). Since the electrical discharge may introduce disturbances in the laminar boundary layer with predetermined intermittency, it was decided to apply this control technique and study the effect of plasma actuators on separated flows on laminar transonic aerofoil.…”

“…The mode of transonic buffet for a laminar regime is featured by smaller amplitude and a significantly higher frequency of the shock wave oscillations in comparison with the turbulent case. The physics of the phenomenon was studied in more detail for the test case of flat plate with incident oblique shock wave at small supersonic Mach numbers in Diop et al, 3 Giepman et al, 4 and Polivanov et al 5 Despite the small differences in these experimental studies, the main results are similar: the turbulent boundary layer does not reduce the drag in the interaction zone; in the laminar bubble pulsations rapidly increase leading to turbulence of the flow; in the laminar bubble complex nonstationary phenomena occur, most probably as a result of the growth of the disturbances due to the intrinsic instability of the separation bubble and shear layer. These conclusions are confirmed by the results of numerical simulation.…”

Подавление Ламинарной Отрывной Зоны Искровым Разрядом При Числе Маха M = 1.43

“…2 представлен результат, полученный при схо-жих условиях в работе [9] для турбулентного состояния набегающего пограничного слоя. Для стационарной турбулизации течения исполь-зовалась зигзагообразная шероховатость, установленная в положении X ≈ 85 mm.…”

“…При этом различные механические турбулизаторы, исследованные для данной конфигурации, не привели к уменьшению потерь полного давления и толщины пограничного слоя в зоне взаимодействия [9].…”