scholarly journals Evolution of turbulence in an oscillatory flow in a smooth-walled channel: A viscous secondary instability mechanism

2003 ◽  
Vol 68 (2) ◽  
Author(s):  
J. A. Cosgrove ◽  
J. M. Buick ◽  
S. J. Tonge
2004 ◽  
Vol 2004.I (0) ◽  
pp. 61-62
Author(s):  
Tatsuo NISHIMURA ◽  
Koji KUNITSUGU ◽  
Akira Okazaki ◽  
Takaki MORIGUTCHI

1991 ◽  
Vol 46 (3) ◽  
pp. 757-771 ◽  
Author(s):  
Tatsuo Nishimura ◽  
Hisashi Miyashita ◽  
Shinichiro Murakami ◽  
Yuji Kawamura

1989 ◽  
Vol 22 (5) ◽  
pp. 505-511 ◽  
Author(s):  
Tatsuo Nishimura ◽  
Hisashi Miyashita ◽  
Shinichiro Murakami ◽  
Yuji Kawamura

2013 ◽  
Vol 728 ◽  
pp. 58-90 ◽  
Author(s):  
Olaf Marxen ◽  
Matthias Lang ◽  
Ulrich Rist

AbstractThe convective primary amplification of a forced two-dimensional perturbation initiates the formation of essentially two-dimensional large-scale vortices in a laminar separation bubble. These vortices are then shed from the bubble with the forcing frequency. Immediately downstream of their formation, the vortices get distorted in the spanwise direction and quickly disintegrate into small-scale turbulence. The laminar–turbulent transition in a forced laminar separation bubble is dominated by this vortex formation and breakup process. Using numerical and experimental data, we give an in-depth characterization of this process in physical space as well as in Fourier space, exploiting the largely periodic character of the flow in time as well as in the spanwise direction. We present evidence that a combination of more than one secondary instability mechanism is active during this process. The first instability mechanism is the elliptic instability of vortex cores, leading to a spanwise deformation of the cores with a spanwise wavelength of the order of the size of the vortex. Another mechanism, potentially an instability of flow in between two consecutive vortices, is responsible for three-dimensionality in the braid region. The corresponding disturbances possess a much smaller spanwise wavelength as compared to those amplified through elliptic instability. The secondary instability mechanisms occur for both fundamental and subharmonic frequency, respectively, even in the absence of continuous forcing, indicative of temporal amplification in the region of vortex formation.


1991 ◽  
Vol 57 (537) ◽  
pp. 1611-1616 ◽  
Author(s):  
Tatsuo NISHIMURA ◽  
Shinichiro MURAKAMI ◽  
Yuji KAWAMURA ◽  
Hisashi MIYASHITA

1993 ◽  
Vol 48 (10) ◽  
pp. 1793-1800 ◽  
Author(s):  
Tatsuo Nishimura ◽  
Shinichiro Murakami ◽  
Yuji Kawamura

1994 ◽  
Vol 273 ◽  
pp. 323-360 ◽  
Author(s):  
Chau-Lyan Chang ◽  
Mujeeb R. Malik

Laminar–turbulent transition mechanisms for a supersonic boundary layer are examined by numerically solving the governing partial differential equations. It is shown that the dominant mechanism for transition at low supersonic Mach numbers is associated with the breakdown of oblique first-mode waves. The first stage in this breakdown process involves nonlinear interaction of a pair of oblique waves with equal but opposite angles resulting in the evolution of a streamwise vortex. This stage can be described by a wave–vortex triad consisting of the oblique waves and a streamwise vortex whereby the oblique waves grow linearly while nonlinear forcing results in the rapid growth of the vortex mode. In the second stage, the mutual and self-interaction of the streamwise vortex and the oblique modes results in the rapid growth of other harmonic waves and transition soon follows. Our calculations are carried all the way into the transition region which is characterized by rapid spectrum broadening, localized (unsteady) flow separation and the emergence of small-scale streamwise structures. The r.m.s. amplitude of the streamwise velocity component is found to be on the order of 4–5 % at the transition onset location marked by the rise in mean wall shear. When the boundary-layer flow is initially forced with multiple (frequency) oblique modes, transition occurs earlier than for a single (frequency) pair of oblique modes. Depending upon the disturbance frequencies, the oblique mode breakdown can occur for very low initial disturbance amplitudes (on the order of 0.001% or even lower) near the lower branch. In contrast, the subharmonic secondary instability mechanism for a two-dimensional primary disturbance requires an initial amplitude on the order of about 0.5% for the primary wave. An in-depth discussion of the oblique-mode breakdown as well as the secondary instability mechanism (both subharmonic and fundamental) is given for a Mach 1.6 flat-plate boundary layer.


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