Flow physics in the turbulent near wake of a flat plate

2013 ◽  
Vol 724 ◽  
pp. 704-733 ◽  
Author(s):  
Man Mohan Rai

AbstractThe symmetric near wake of a flat plate with a circular trailing edge, exhibiting pronounced shedding of wake vortices, is investigated via a direct numerical simulation. The separating plate boundary layers are turbulent and statistically identical. The present study focuses on the vortical structures, the distribution of phase-averaged velocity statistics and vorticity fluctuations in the near wake. Braid and vortex core regions are investigated via contours of instantaneous vorticity and pressure with an emphasis on the three-dimensionality of near-wake structures. Rib vortices are observed in the braids. The vortex cores are populated with both ribs that wrap themselves around the cores and spanwise-elongated regions of spanwise vorticity near the centres of the cores. Production terms in the transport equations for phase-averaged fluctuating vorticity show that stretching of rib vortices via the phase-averaged strain rate produces significantly less turbulent vorticity than turbulent stretching in the braids and cores.

1995 ◽  
Vol 298 ◽  
pp. 211-248 ◽  
Author(s):  
U. Rist ◽  
H. Fasel

The three-dimensional development of controlled transition in a flat-plate boundary layer is investigated by direct numerical simulation (DNS) using the complete Navier-Stokes equations. The numerical investigations are based on the so-called spatial model, thus allowing realistic simulations of spatially developing transition phenomena as observed in laboratory experiments. For solving the Navier-Stokes equations, an efficient and accurate numerical method was developed employing fourth-order finite differences in the downstream and wall-normal directions and treating the spanwise direction pseudo-spectrally. The present paper focuses on direct simulations of the wind-tunnel experiments by Kachanov et al. (1984, 1985) of fundamental breakdown in controlled transition. The numerical results agreed very well with the experimental measurements up to the second spike stage, in spite of relatively coarse spanwise resolution. Detailed analysis of the numerical data allowed identification of the essential breakdown mechanisms. In particular, from our numerical data, we could identify the dominant shear layers and vortical structures that are associated with this breakdown process.


2019 ◽  
Vol 196 ◽  
pp. 00017
Author(s):  
Aleksey Yatskikh ◽  
Aleksander Semenov ◽  
Gleb Kolosov ◽  
Aleksander Kosinov ◽  
Yury Yermolaev

The influence of the parameters of the impulse action on the laminar supersonic flat-plate boundary layer on the excited localized perturbations is investigated at Mach 2. The influence of the duration of a pulsed discharge on the generated disturbances is studied experimentally. Also, a direct numerical simulation of the influence of the parameters of pulse injection on generated perturbations is carried out. It is obtained that as the duration of the action on the supersonic boundary layer increases, the amplitude of the generated disturbance increases. The velocity of the propagation downstream of localized disturbances in Mach 2 supersonic flat-plate boundary layer is estimated.


2000 ◽  
Vol 12 (10) ◽  
pp. 2555 ◽  
Author(s):  
Hojin Kong ◽  
Haecheon Choi ◽  
Joon Sik Lee

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