scholarly journals Cross-correlation measurement of disturbance initiated by weak shock wave in the flat plate boundary layer with blunt leading edge at Mach 2

2021 ◽  
Author(s):  
L. V. Afanasev ◽  
A. D. Kosinov ◽  
A. A. Yatskikh ◽  
V. L. Kocharin ◽  
N. V. Semionov ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Flat Plate ◽  
Cross Correlation ◽  
Plate Boundary ◽  
Leading Edge ◽  
Weak Shock ◽  
Weak Shock Wave ◽  
Blunt Leading Edge ◽  
Flat Plate Boundary Layer

Numerical Study of Nanosecond Pulsed Plasma Actuator in Laminar Flat Plate Boundary Layer

2016 ◽  
Vol 20 (5) ◽  
pp. 1424-1442 ◽  
Author(s):  
J. G. Zheng ◽  
J. Li ◽  
Z. J. Zhao ◽  
Y. D. Cui ◽  
B. C. Khoo
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Flat Plate ◽  
Numerical Study ◽  
Wave Train ◽  
Plate Boundary ◽  
Flow Separation Control ◽  
Strong Control ◽  
Flat Plate Boundary Layer ◽  
Residual Heat

AbstractNanosecond (ns) pulsed dielectric barrier discharge (DBD) actuator in a laminar flat plate boundary layer is investigated numerically in an attempt to gain some new insights into the understanding of ns DBD actuation mechanism. Special emphasis is put on the examination, separation and comparison of behaviors of discharge induced micro shock wave and residual heat as well as on the investigation of response of external flow to the two effects. The shock wave is found to introduce highly transient, localized perturbation to the flow and be able to significantly alter the flow pattern shortly after its initiation. The main flow tends to quickly recover to close to its undisturbed state due to the transient nature of perturbation. However, with the shock decay and final disappearance, another perturbation source in the vicinity of discharge region, which contains contribution from both residual heat and shock, becomes increasingly pronounced and eventually develops into a perturbation wave train in the boundary layer. The perturbation is relatively weak and may not be a Tollmien-Schlichting (TS) wave and not trigger the laminar-turbulent transition of boundary layer. Instead, it is more likely to manipulate the flow stability to achieve the strong control authority of this kind of actuation in the case of flow separation control. In addition, a parametric study over the different electrical and hydrodynamic parameters is also conducted.

scholarly journals The experimental study of the weak shock wave action on the boundary layer of the sweep flat plate

2019 ◽  
Vol 1404 ◽  
pp. 012083
Author(s):  
V L Kocharin ◽  
A D Kosinov ◽  
A A Yatskikh ◽  
L V Afanasev ◽  
Yu G Ermolaev ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Experimental Study ◽  
Flat Plate ◽  
Weak Shock ◽  
Wave Action ◽  
Weak Shock Wave

scholarly journals Streamwise counter-rotating vortices generated by triangular leading edge pattern in flat plate boundary layer

2016 ◽  
Vol 19 (3) ◽  
pp. 359-367 ◽  
Author(s):  
S. M. Hasheminejad ◽  
H. Mitsudharmadi ◽  
S. H. Winoto ◽  
K. B. Lua ◽  
H. T. Low
Keyword(s):  
Boundary Layer ◽  
Flat Plate ◽  
Plate Boundary ◽  
Leading Edge ◽  
Flat Plate Boundary Layer ◽  
Edge Pattern

scholarly journals Experimental Study of the Weak Shock Wave Action on the Boundary Layer of a Plate at the Mach Number 2.5

2019 ◽  
Vol 14 (2) ◽  
pp. 46-55 ◽  
Author(s):  
V. L. Kocharin ◽  
A. A. Yatskikh ◽  
A. D. Kosinov ◽  
Yu. G. Yermolaev ◽  
N. V. Semionov
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Experimental Study ◽  
Mach Number ◽  
Side Wall ◽  
Leading Edge ◽  
Weak Shock ◽  
Supersonic Boundary Layer ◽  
Weak Shock Wave ◽  
Frequency Spectra

Experimental study of the effect of a weak shock wave from the protuberance of two-dimensional roughness installed on the side wall of the test section of the wind tunnel on the supersonic boundary layer of the blunted flat plate at the Mach number 2.5 was carried out. The measurements were performed by a constant temperature hot-wire anemometer in the region of stream wise vortices generated by the shock wave from the protuberance during interaction with the flow in the vicinity of the leading edge of the model. The spectral and statistical analyses of the measured disturbances in the boundary layer were carried out. The amplitude-frequency spectra of mass flow pulsations and statistical diagrams of the measured disturbances in the supersonic part of the boundary layer were obtained.

Effect of a Triangular Rib on a Flat Plate Boundary Layer

2015 ◽  
Vol 138 (1) ◽  
Author(s):  
F. Fouladi ◽  
P. Henshaw ◽  
D. S.-K. Ting
Keyword(s):  
Boundary Layer ◽  
Wind Tunnel ◽  
Flat Plate ◽  
Turbulence Intensity ◽  
Plate Boundary ◽  
Leading Edge ◽  
Smooth Wall ◽  
Turbulence Length ◽  
Turbulence Parameters ◽  
Flat Plate Boundary Layer

The flow structure downstream of a triangular rib over a thin plate placed in a wind tunnel was experimentally investigated using a boundary layer hotwire anemometer. Flow and boundary layer characteristics, such as thickness, shape, and turbulence parameters, were studied at different freestream velocities and streamwise locations corresponding to ReX of 1.7 × 104–2.8 × 105 for plates without and with a leading edge rib. It was found that the boundary layer of the flow over a ribbed wall was 3–3.5 times thicker and had higher turbulence intensity and smaller turbulence length scales compared to its smooth wall counterpart.

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