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
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
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
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
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: National Aeronautics and Space Adm Nasa Publisher: Independently Published ISBN: 9781792705748 Category : Languages : en Pages : 30
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: Alexander J. Smits Publisher: A I P Press ISBN: Category : Science Languages : en Pages : 384
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: Doyle Knight
Author: Doyle Knight
Author: Hong Yan
Author: 
Author: Kamlesh Kapoor
Author: Gerald Urbin
Author: National Aeronautics and Space Adm Nasa
Author: Somnath Ghosh
Author: Gerald Urbin
Author: Alexander J. Smits
Author: D. Knight