A numerical study on the natural transition locations in the flat-plate boundary layers on superhydrophobic surfaces

2020 ◽  
Vol 32 (12) ◽  
pp. 124103
Author(s):  
Bin Liu ◽  
Yongming Zhang
Keyword(s):  
Flat Plate ◽  
Boundary Layers ◽  
Numerical Study ◽  
Plate Boundary ◽  
Superhydrophobic Surfaces

NUMERICAL STUDY OF THE DISTURBANCES GENERATED BY MICROJETS IN A SUPERSONIC FLAT PLATE BOUNDARY LAYER

2021 ◽  
Author(s):  
Andrei Valerievich Novikov ◽  
Alexander Vitalievich Fedorov ◽  
Ivan Vladimirovich Egorov ◽  
Anton Olegovich Obraz ◽  
Nikolay Nikolaevich Semenov
Keyword(s):  
Boundary Layer ◽  
Flat Plate ◽  
Numerical Study ◽  
Plate Boundary ◽  
Flat Plate Boundary Layer

A study in transitional flat plate boundary layers: measurement and visualization

2000 ◽  
Vol 28 (3) ◽  
pp. 243-251 ◽  
Author(s):  
C. B. Lee ◽  
Z. X. Hong ◽  
Y. S. Kachanov ◽  
V. I. Borodulin ◽  
V. V. Gaponenko
Keyword(s):  
Flat Plate ◽  
Boundary Layers ◽  
Plate Boundary

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 Video: The Hitchhiker's Guide to Flat Plate Boundary Layers

2020 ◽  
Author(s):  
Joshua Lee ◽  
Guillaume Blanquart ◽  
Joseph Ruan
Keyword(s):  
Flat Plate ◽  
Boundary Layers ◽  
Plate Boundary

Large-Eddy Simulation of Corner Separation in a Compressor Cascade

2018 ◽  
Author(s):  
Byung-Young Min ◽  
Jongwook Joo ◽  
Jomar Mendoza ◽  
Jin Lee ◽  
Guoping Xia ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Flat Plate ◽  
Boundary Layers ◽  
Best Practice ◽  
Plate Boundary ◽  
Leading Edge ◽  
Horseshoe Vortex ◽  
Compressor Cascade ◽  
Corner Separation ◽  
Institute Of Technology

In this paper, wall-resolved LES computations for a compressor cascade from Ecole Centrale de Lyon [1] are presented. A computational grid containing about 600 million computational cells was used in these simulations. This grid resolves the details of tripping strips used in the experiments, located near the leading edge of the blade on both suction and pressure sides. Endwall turbulent boundary layer at cascade inlet was measured to be at a momentum thickness based Reynolds number of about 7000 to 8000, with quite a bit of variation in the pitchwise direction. In order to avoid the cost of simulating the entire duct upstream of the cascade, and any auxiliary flat plate boundary layer simulations, the inlet fluctuations for LES computations were generated using digital filtering method for synthetic turbulence generation [27]. Turbulence statistics from a database of high fidelity eddy simulations of flat plate boundary layers (at similar Reynolds numbers) from KTH Royal Institute of Technology in Stockholm [28] were used to fully define the properties of the cascade inlet boundary layer. In this paper, time-averaged results from three LES computations for this configuration are presented — one with no inlet fluctuations at the cascade endwall at the domain inlet, and then two computations with inlet fluctuations and boundary layers at Reθ of 7000 and 8183. These provide a sensitivity of LES predictions of corner separation in the cascade to the boundary layer thickness at cascade inlet. A comparison of these simulations with prior DDES (and RANS) simulations from UTRC [26], as well as existing LES results from Ecole Centrale de Lyon [12], allows to further the understanding of critical elements of the endwall flow physics. More specifically, it provides more insight into which phenomena need to be sufficiently resolved (e.g. horseshoe vortex) in order to capture both the average behavior of the corner separation, as well as its unsteady dynamics. In addition, it provides new information which will help define best practice guidelines for the use of eddy simulations to resolve endwall features in compressors at off-design conditions.

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