Large Eddy Simulation of a Supersonic Compression Corner PDF Download
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Author: Gerald Urbin
Publisher:
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Languages : en
Pages :
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Author: Gerald Urbin
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Hong Yan
Publisher:
ISBN:
Category :
Languages : en
Pages : 8
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Book Description
A Large Eddy Simulation of a 25 deg compression corner at M = 2.88 and Re(delta) - 2 x 10(exp 4) is performed using an Essentially Non Oscillatory (ENO) scheme. The Favre filtered compressible Navier-Stokes equations are solved using a Monotone Integrated Large Eddy Simulation (MILES) technique on an unstructured grid of tetrahedral cells. The mean flow variables and turbulent shear stress at the incoming flow are in good agreement with experiment and DNS. The separation length scaled by the characteristic scale shows agreement with the experiment. No pronounced pressure plateau is observed compared with experiment at higher Reynolds number.
Author: Doyle Knight
Publisher:
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Languages : en
Pages : 12
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A Large Eddy Simulation (LES) methodology has been developed for supersonic turbulent flows with strong shock boundary layer interaction. Results are presented for an expansion-compression corner at Mach 3 and compared with experimental data.
Author:
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Languages : en
Pages : 0
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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: Donald P. Rizzetta
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Languages : en
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Author: Kamlesh Kapoor
Publisher:
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Category :
Languages : en
Pages : 18
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781792705748
Category :
Languages : en
Pages : 30
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Book Description
A two-dimensional computational code, PRLUS2D, which was developed for the reactive propulsive flows of ramjets and scramjets, was validated for two-dimensional shock-wave/turbulent-boundary-layer interactions. The problem of compression corners at supersonic speeds was solved using the RPLUS2D code. To validate the RPLUS2D code for hypersonic speeds, it was applied to a realistic hypersonic inlet geometry. Both the Baldwin-Lomax and the Chien two-equation turbulence models were used. Computational results showed that the RPLUS2D code compared very well with experimentally obtained data for supersonic compression corner flows, except in the case of large separated flows resulting from the interactions between the shock wave and turbulent boundary layer. The computational results compared well with the experiment results in a hypersonic NASA P8 inlet case, with the Chien two-equation turbulence model performing better than the Baldwin-Lomax model. Kapoor, Kamlesh and Anderson, Bernhard H. and Shaw, Robert J. Glenn Research Center NASA-TM-106580, E-8840, NAS 1.15:106580 RTOP 537-02-23...
Author: Gerald Urbin
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Category :
Languages : en
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Author: Chaoqun Liu
Publisher: Bentham Science Publishers
ISBN: 1681085976
Category : Technology & Engineering
Languages : en
Pages : 321
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This volume presents an implicitly implemented large eddy simulation (ILES) by using the fifth order bandwidth-optimized WENO scheme. The chosen method is applied to make comprehensive studies on ramp flows with and without control at Mach 2.5 and Re=5760. Flow control in the form of microramp vortex generators (MVG) is applied. The results show that a MVG can distinctly reduce the separation zone at the ramp corner and lower the boundary layer shape factor under simulated conditions. A series of new findings about the MVG-ramp flow are obtained, including structures relevant to surface pressure, three-dimensional structures of the re-compression shock waves, a complete surface separation pattern, momentum deficit and a new secondary vortex system. A new mechanism of shock-boundary layer interaction control by MVG associated with a series of vortex rings is also presented. Vortex rings strongly interact with air flow and play an important role in the separation zone reduction. Additionally, readers will learn about the governing equation, boundary condition, high quality grid generation, high order shock capturing scheme and DNS inflow condition in detail. This volume will, therefore, serve as a useful reference for aerospace researchers using LES methods to study shock boundary layer interaction and supersonic flow control.
Author:
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ISBN:
Category :
Languages : en
Pages : 40
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Book Description
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 tetrahedra. 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 flow fields have been computed: supersonic flat plate boundary layer, supersonic compression corner, supersonic expansion-compression corner and subsonic square jet. The computed results show close agreement with experiment and Direct Numerical Simulation, and validate the unstructured grid LES methodology.
