Numerical Investigation of Cross-flow Instability of a Flat Plate Boundary Layer with Abrupt Spanwise Wall Motion

2022 ◽  
Author(s):  
Md Kamrul Hasan ◽  
Andreas Gross
Keyword(s):  
Boundary Layer ◽  
Flat Plate ◽  
Numerical Investigation ◽  
Wall Motion ◽  
Flow Instability ◽  
Plate Boundary ◽  
Cross Flow ◽  
Flat Plate Boundary Layer

The control of transient disturbances in a flat plate boundary layer through active wall motion

1989 ◽  
Vol 1 (3) ◽  
pp. 574-582 ◽  
Author(s):  
Kenneth S. Breuer ◽  
Joseph H. Haritonidis ◽  
Marten T. Landahl
Keyword(s):  
Boundary Layer ◽  
Flat Plate ◽  
Wall Motion ◽  
Plate Boundary ◽  
Transient Disturbances ◽  
Flat Plate Boundary Layer

scholarly journals Experimental and numerical investigation of excitation of artificial disturbances in the supersonic boundary layer

2019 ◽  
Vol 196 ◽  
pp. 00017
Author(s):  
Aleksey Yatskikh ◽  
Aleksander Semenov ◽  
Gleb Kolosov ◽  
Aleksander Kosinov ◽  
Yury Yermolaev
Keyword(s):  
Numerical Simulation ◽  
Boundary Layer ◽  
Direct Numerical Simulation ◽  
Flat Plate ◽  
Numerical Investigation ◽  
Plate Boundary ◽  
Supersonic Boundary Layer ◽  
Pulsed Discharge ◽  
Pulse Injection ◽  
Flat Plate Boundary Layer

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.

Effect of Velocity Ratio on Vortex Shedding From a Short Stack

2006 ◽  
Author(s):  
M. S. Adaramola ◽  
A. O. Oladeinde ◽  
D. Sumner ◽  
D. J. Bergstrom
Keyword(s):  
Boundary Layer ◽  
Flat Plate ◽  
Flow Regime ◽  
Strouhal Number ◽  
Vortex Shedding ◽  
Velocity Ratio ◽  
Plate Boundary ◽  
Cross Flow ◽  
Flow Regimes ◽  
Flat Plate Boundary Layer

The influence of the jet-to-cross-flow velocity ratio, R, on vortex shedding from a cylindrical stack of aspect ratio AR = 9 was investigated using hot-wire anemometry. The cross-flow Reynolds number was ReD = 2.3×104 and R was varied from 0 to 3. The stack was partially immersed in a flat-plate boundary layer, where the boundary layer thickness-to-height ratio at the location of the stack was δ/H = 0.5. In the downwash flow regime, when R < 0.7, a single Strouhal number (e.g., St = 0.167 at R = 0) was measured along the entire stack height. In the crosswind-dominated flow regime, when 0.7 ≤ R < 1.5, a higher Strouhal number was obtained (e.g., St = 0.185 at R = 1.0). In the transitional and jet-dominated flow regimes, a jump in Strouhal number (e.g., from St = 0.176 to 0.193 at R = 2.0), occurred within the flat-plate boundary layer. The power spectra showed that the shape and strength of the vortex shedding peak changed along the stack height. In general, the peak was more broad-banded near the base of the stack, became sharper and more distinct within the middle of the combined stack and jet wakes, and then reduced in strength in the jet wake and jet regions. In the transitional and jet-dominated flow regimes, the jump in Strouhal number was seen as a gradual change in dominance between two closely spaced peaks, with both peaks co-existing near the edge of the boundary layer.

Interaction of intersecting shocks with a flat-plate boundary layer in the presence of an entropy layer

2013 ◽  
Vol 48 (5) ◽  
pp. 636-647 ◽  
Author(s):  
V. Ya. Borovoy ◽  
I. V. Egorov ◽  
V. E. Mosharov ◽  
V. N. Radchenko ◽  
A. S. Skuratov ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Flat Plate ◽  
Plate Boundary ◽  
Entropy Layer ◽  
Flat Plate Boundary Layer
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