Zonal detached eddy simulation (ZDES) of a spatially developing flat plate turbulent boundary layer over the Reynolds number range 3 150 ⩽Reθ⩽ 14 000

2014 ◽  
Vol 26 (2) ◽  
pp. 025116 ◽  
Author(s):  
Sébastien Deck ◽  
Nicolas Renard ◽  
Romain Laraufie ◽  
Pierre Sagaut
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Turbulent Boundary Layer ◽  
Flat Plate ◽  
Detached Eddy Simulation ◽  
Number Range ◽  
Eddy Simulation ◽  
Reynolds Number Range

Heat transfer from a hypersonic turbulent boundary layer on a flat plate

1973 ◽  
Vol 60 (2) ◽  
pp. 257-271 ◽  
Author(s):  
G. T. Coleman ◽  
C. Osborne ◽  
J. L. Stollery
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Reynolds Number ◽  
Friction Coefficient ◽  
Mach Number ◽  
Turbulent Boundary Layer ◽  
Flat Plate ◽  
Reasonable Agreement ◽  
Skin Friction Coefficient ◽  
Number Range

A hypersonic gun tunnel has been used to measure the heat transfer to a sharpedged flat plate inclined at various incidences to generate local Mach numbers from 3 to 9. The measurements have been compared with a number of theoretical estimates by plotting the Stanton number against the energy-thickness Reynolds number. The prediction giving the most reasonable agreement throughout the above Mach number range is that due to Fernholz (1971).The values of the skin-friction coefficient derived from velocity profiles and Preston tube data are also given.

Zonal Detached Eddy Simulation of a spatially developing flat plate turbulent boundary layer

2011 ◽  
Vol 48 (1) ◽  
pp. 1-15 ◽  
Author(s):  
Sébastien Deck ◽  
Pierre-Élie Weiss ◽  
Mathieu Pamiès ◽  
Eric Garnier
Keyword(s):  
Boundary Layer ◽  
Turbulent Boundary Layer ◽  
Flat Plate ◽  
Detached Eddy Simulation ◽  
Eddy Simulation

Unsteady Simulations for an Advanced-Louver Cooling Scheme

2008 ◽  
Author(s):  
Chad X.-Z. Zhang ◽  
Sung In Kim ◽  
Ibrahim G. Hassan
Keyword(s):  
Reynolds Number ◽  
Wind Tunnel ◽  
Flat Plate ◽  
Flow Velocity ◽  
Detached Eddy Simulation ◽  
Computer Cluster ◽  
Vortical Structures ◽  
Eddy Simulation ◽  
Mainstream Flow ◽  
Adiabatic Effectiveness

The performance of a louver cooling scheme on a flat plate was analyzed using Detached Eddy Simulation. It was assumed that the louver cooling scheme was tested in a wind tunnel with the mainstream flow velocity of 20 m/s, equivalent to a Reynolds number of 16200 based on the jet diameter. Turbulence closure was achieved by a Realizable k-ε based DES turbulence model. Solutions of two blowing ratios of 0.5 and 1 were successfully obtained by running parallel on 16 nodes on a computer cluster. The instantaneous flow fields were found to be highly unsteady and oscillatory in nature. It is shown that the fluctuations in the adiabatic effectiveness are mainly caused by the spanwise fluctuation of the coolant jet and the unsteady vortical structures created by the interaction of the jet and the mainstream.

scholarly journals Some hypersonic intake studies

2006 ◽  
Vol 110 (1105) ◽  
pp. 145-156 ◽  
Author(s):  
F. Lanson ◽  
J. L. Stollery
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Layer Growth ◽  
Isentropic Compression ◽  
Number Range ◽  
Principal Influence ◽  
Reynolds Number Range ◽  
Air Intake ◽  
Starting Process ◽  
Intake Flow

Abstract A ‘two dimensional’ air intake comprising a wedge followed by an isentropic compression has been tested in the Cranfield Gun Tunnel at Mach 8·2. These tests were performed to investigate qualitatively the intake flow starting process. The effects of cowl position, Reynolds number, boundary-layer trip and introduction of a small restriction in the intake duct were investigated. Schlieren pictures of the flow on the compression surface and around the intake entrance were taken. Results showed that the intake would operate over the Reynolds number range tested. Tests with a laminar boundary layer demonstrated the principal influence of the Reynolds number on the boundary-layer growth and consequently on the flow structure in the intake entrance. In contrast boundary layer tripping produced little variation in flow pattern over the Reynolds number range tested. The cowl lip position appeared to have a strong effect on the intake performance. The only parameter which prevented the intake from starting was the introduction of a restriction in the intake duct. The experimental data obtained were in good qualitative agreement with the CFD predictions. Finally, these experimental results indicated a good intake flow starting process over multiple changes of parameters.

Bubble friction drag reduction in a high-Reynolds-number flat-plate turbulent boundary layer

2006 ◽  
Vol 552 (-1) ◽  
pp. 353 ◽  
Author(s):  
WENDY C. SANDERS ◽  
ERIC S. WINKEL ◽  
DAVID R. DOWLING ◽  
MARC PERLIN ◽  
STEVEN L. CECCIO
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Turbulent Boundary Layer ◽  
Drag Reduction ◽  
Flat Plate ◽  
High Reynolds Number ◽  
Friction Drag ◽  
High Reynolds ◽  
Friction Drag Reduction

Wall-Modeled LES for Ship Hydrodynamics in Model Scale

2020 ◽  
pp. 1-14
Author(s):  
Mattias Liefvendahl ◽  
Mattias Johansson
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Turbulent Boundary Layer ◽  
Predictive Accuracy ◽  
Computational Cost ◽  
Bulk Carrier ◽  
Ship Hydrodynamics ◽  
Model Scale ◽  
Eddy Simulation ◽  
Large Eddy

A complete approach for wall-modeled large-eddy simulation (WMLES) is demonstrated for the simulation of the flow around a bulk carrier in the model scale. Essential components of the method are an a-priori estimate of the thickness of the turbulent boundary layer (TBL) over the hull and to use an unstructured grid with the appropriate resolution relative to this thickness. Expressions from the literature for the scaling of the computational cost, in terms of the grid size, with Reynolds number, are adapted in this application. It is shown that WMLES is possible for model scale ship hydrodynamics, with ∼108 grid cells, which is a gain of at least one order of magnitude as compared with wall-resolving LES. For the canonical case of a flat-plate TBL, the effects of wall model parameters and grid cell topology on the predictive accuracy of the method are investigated. For the flat-plate case, WMLES results are compared with results from direct numerical simulation, RANS (Reynolds-averaged Navier-Stokes), and semi-empirical formulas. For the bulk carrier flow, WMLES and RANS are compared, but further validation is needed to assess the predictive accuracy of the approach. 1. Introduction The number of applications of large-eddy simulation (LES) and other scale-resolving approaches, such as detached-eddy simulation and different forms of RANS-LES hybrids, is steadily increasing in naval hydrodynamics (Larsson et al. 2014; Fureby 2017). The importance of the hull boundary layer and the implications in terms of grid resolution requirements (and associated computational cost) for different turbulence modeling approaches is what mainly limits the application of LES in ship hydrodynamics (Liefvendahl & Fureby 2017). Wall-resolving LES (WRLES), in which the energetic flow structures in the inner part of the turbulent boundary layer (TBL) are resolved, puts excessive requirements on the grid resolution. Recently, the first model scale simulations using WRLES were reported (Nishikawa 2015; Posa & Balaras 2018). In these simulations, >109 grid points were necessary, even at low model scale Reynolds number. For full-scale simulations, WRLES is out of range of present computational resources (Liefvendahl & Fureby 2017).

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