Large Eddy Simulations of Supersonic Flat Plate Boundary Layer PDF Download
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Author: H. Yan
Publisher:
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Languages : en
Pages :
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Author: H. Yan
Publisher:
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Category :
Languages : en
Pages :
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Author: H. Shan
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Category :
Languages : en
Pages :
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Author: Y. H. Chong
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Category :
Languages : en
Pages : 0
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Author:
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Category :
Languages : en
Pages : 0
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Book Description
The focus of the grant was the use of Application Visualization System (AVS), developed by Advanced Visual Systems, Inc., for animating supersonic turbulent flows computed using Large Eddy Simulation (LES) . Three flow configurations are visualized: a turbulent flat plate supersonic boundary layer, an 8 deg supersonic compression corner and a 25 deg supersonic compression corner. The animations display the quantitative and qualitative features of the turbulence production and the complex physics of the shock wave turbulent boundary layer interaction.
Author: Y.H Chong
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Category :
Languages : en
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Author: Holger Babinsky
Publisher: Cambridge University Press
ISBN: 1139498649
Category : Technology & Engineering
Languages : en
Pages : 481
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Book Description
Shock wave-boundary-layer interaction (SBLI) is a fundamental phenomenon in gas dynamics that is observed in many practical situations, ranging from transonic aircraft wings to hypersonic vehicles and engines. SBLIs have the potential to pose serious problems in a flowfield; hence they often prove to be a critical - or even design limiting - issue for many aerospace applications. This is the first book devoted solely to a comprehensive, state-of-the-art explanation of this phenomenon. It includes a description of the basic fluid mechanics of SBLIs plus contributions from leading international experts who share their insight into their physics and the impact they have in practical flow situations. This book is for practitioners and graduate students in aerodynamics who wish to familiarize themselves with all aspects of SBLI flows. It is a valuable resource for specialists because it compiles experimental, computational and theoretical knowledge in one place.
Author: Y. H. Chong
Publisher:
ISBN:
Category :
Languages : en
Pages : 170
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Author: M. Lesieur
Publisher: Cambridge University Press
ISBN: 9780521781244
Category : Mathematics
Languages : en
Pages : 240
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Large-Eddy Simulations of Turbulence is a reference for LES, direct numerical simulation and Reynolds-averaged Navier-Stokes simulation.
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Languages : en
Pages : 0
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The interaction of a shock wave with a turbulent boundary layer is a central problem in supersonic inlet flows. This work uses numerical and analytical techniques to study shock/turbulence interaction in order to identify and explain factors important in shock/boundary layer interaction. Direct numerical simulation of a normal shock wave with an isotropic turbulent field of vorticity and entropy fluctuations showed that negative upstream correlation between the vorticity and entropy fluctuations enhances the turbulence across the shock. Positive upstream correlation has a suppressing effect. A new numerical method providing excellent high wavenumber resolution while reducing the computational cost was developed. A model with no adjustable constants was developed to study the vortex breakdown resulting from the interaction of canard or forbody vortices with the shock waves in a supersonic inlet flow. Very good agreement with both experiment and computation was obtained. A numerical method to compute shock/turbulence interaction using a conservative form of the Large Eddy Simulation (LES) equations has been developed and validated. LES of the interaction of isotropic turbulence with a normal shock was performed and comparisons with direct numerical simulation (DNS) results were favorable. A new Fortran 90 code has been developed for the computation of shock/turbulence interaction. The code is an improved version of codes used previously in shock/turbulence interaction simulations.
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Languages : en
Pages : 0
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An unstructured grid Large Eddy Simulation (LES) methodology has been developed for compressible high speed flows. The filtered compressible Navier-Stokes equations are solved on an unstructured grid of tetrahera. The inviscid fluxes are obtained from an exact locally one-dimensional Riemann solver using Godunov's method. The viscous fluxes are obtained using a discrete analog of Gauss' Theorem. The reconstruction is performed using a Least Squares technique. The temporal integration is a Runge-Kutta method. The algorithm is overall second order accurate in space and time. Four flowfields have been computed: decay of isotropic turbulence, channel flow, supersonic flat plate boundary layer and supersonic compression corner. The first and second cases are effectively incompressible, while the third and fourth cases are supersonic (Mach 3). The computed results show close agreement with experiment and Direct Numerical Simulation and validate the unstructured grid LES methodology.
