Large Eddy Simulation of Supersonic Turbulent Flow in Expansion-Compression Corner PDF Download
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Author: Doyle Knight
Publisher:
ISBN:
Category :
Languages : en
Pages : 12
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Book Description
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: Doyle Knight
Publisher:
ISBN:
Category :
Languages : en
Pages : 12
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Book Description
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: 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:
Publisher:
ISBN:
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: Kamlesh Kapoor
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
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Author: Gerald Urbin
Publisher:
ISBN:
Category :
Languages : en
Pages :
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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: Somnath Ghosh
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Author: Gerald Urbin
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Alexander J. Smits
Publisher: A I P Press
ISBN:
Category : Science
Languages : en
Pages : 384
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Book Description
Using the most recent data, this text describes the physical mechanisms of turbulent supersonic flows, emphasizing the similarities and differences between compressible and incompressible flows. DLC: Aerodynamics, Supersonic.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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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 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.
