Wind-Us Code Contributions to the First AIAA Shock Boundary Layer Interaction Prediction Workshop PDF Download
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781793962911
Category : Science
Languages : en
Pages : 32
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Book Description
This report discusses the computations of a set of shock wave/turbulent boundary layer interaction (SWTBLI) test cases using the Wind-US code, as part of the 2010 American Institute of Aeronautics and Astronautics (AIAA) shock/boundary layer interaction workshop. The experiments involve supersonic flows in wind tunnels with a shock generator that directs an oblique shock wave toward the boundary layer along one of the walls of the wind tunnel. The Wind-US calculations utilized structured grid computations performed in Reynolds-averaged Navier-Stokes mode. Four turbulence models were investigated: the Spalart-Allmaras one-equation model, the Menter Baseline and Shear Stress Transport k-omega two-equation models, and an explicit algebraic stress k-omega formulation. Effects of grid resolution and upwinding scheme were also considered. The results from the CFD calculations are compared to particle image velocimetry (PIV) data from the experiments. As expected, turbulence model effects dominated the accuracy of the solutions with upwinding scheme selection indicating minimal effects. Georgiadis, Nicholas J. and Vyas, Manan A. and Yoder, Dennis A. Glenn Research Center WBS 599489.02.07.03.03.13.01
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781793962911
Category : Science
Languages : en
Pages : 32
Get Book Here
Book Description
This report discusses the computations of a set of shock wave/turbulent boundary layer interaction (SWTBLI) test cases using the Wind-US code, as part of the 2010 American Institute of Aeronautics and Astronautics (AIAA) shock/boundary layer interaction workshop. The experiments involve supersonic flows in wind tunnels with a shock generator that directs an oblique shock wave toward the boundary layer along one of the walls of the wind tunnel. The Wind-US calculations utilized structured grid computations performed in Reynolds-averaged Navier-Stokes mode. Four turbulence models were investigated: the Spalart-Allmaras one-equation model, the Menter Baseline and Shear Stress Transport k-omega two-equation models, and an explicit algebraic stress k-omega formulation. Effects of grid resolution and upwinding scheme were also considered. The results from the CFD calculations are compared to particle image velocimetry (PIV) data from the experiments. As expected, turbulence model effects dominated the accuracy of the solutions with upwinding scheme selection indicating minimal effects. Georgiadis, Nicholas J. and Vyas, Manan A. and Yoder, Dennis A. Glenn Research Center WBS 599489.02.07.03.03.13.01
Author: Nicholas J. Georgiadis
Publisher:
ISBN:
Category :
Languages : en
Pages : 6
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Book Description
Author: Nicholas J. Georgiadis
Publisher: BiblioGov
ISBN: 9781289269517
Category :
Languages : en
Pages : 34
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Book Description
The NASA Technical Reports Server (NTRS) houses half a million publications that are a valuable means of information to researchers, teachers, students, and the general public. These documents are all aerospace related with much scientific and technical information created or funded by NASA. Some types of documents include conference papers, research reports, meeting papers, journal articles and more. This is one of those documents.
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: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781793956316
Category : Science
Languages : en
Pages : 38
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Book Description
This paper documents the CFL3D contribution to the AIAA Supersonic Shock Boundary Layer Interaction Workshop, held in Orlando, Florida in January 2010. CFL3D is a Reynolds-averaged Navier-Stokes code. Four shock boundary layer interaction cases are computed using a one-equation turbulence model widely used for other aerodynamic problems of interest. Two of the cases have experimental data available at the workshop, and two of the cases do not. The effect of grid, flux scheme, and thin-layer approximation are investigated. Comparisons are made to the available experimental data. All four cases exhibit strong three-dimensional behavior in and near the interaction regions, resulting from influences of the tunnel side-walls. Rumsey, Christopher L. Langley Research Center NASA/TM-2010-216858, L-19922, NF1676L-11451
Author: National Aeronaut Administration (Nasa)
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
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Book Description
This paper documents the CFL3D contribution to the AIAA Supersonic Shock Boundary Layer Interaction Workshop, held in Orlando, Florida in January 2010. CFL3D is a Reynolds-averaged Navier-Stokes code. Four shock boundary layer interaction cases are computed using a one-equation turbulence model widely used for other aerodynamic problems of interest. Two of the cases have experimental data available at the workshop, and two of the cases do not. The effect of grid, flux scheme, and thin-layer approximation are investigated. Comparisons are made to the available experimental data. All four cases exhibit strong three-dimensional behavior in and near the interaction regions, resulting from influences of the tunnel side-walls. Rumsey, Christopher L. Langley Research Center NASA/TM-2010-216858, L-19922, NF1676L-11451 WBS 561581.02.08.07.20.14 SHOCK LAYERS; SUPERSONIC BOUNDARY LAYERS; TURBULENCE MODELS; MATHEMATICAL MODELS; COMPUTATIONAL FLUID DYNAMICS; NAVIER-STOKES EQUATION; WALLS
Author: Christopher L. Rumsey
Publisher: BiblioGov
ISBN: 9781289180003
Category :
Languages : en
Pages : 40
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Book Description
This paper documents the CFL3D contribution to the AIAA Supersonic Shock Boundary Layer Interaction Workshop, held in Orlando, Florida in January 2010. CFL3D is a Reynolds-averaged Navier-Stokes code. Four shock boundary layer interaction cases are computed using a one-equation turbulence model widely used for other aerodynamic problems of interest. Two of the cases have experimental data available at the workshop, and two of the cases do not. The effect of grid, flux scheme, and thin-layer approximation are investigated. Comparisons are made to the available experimental data. All four cases exhibit strong three-dimensional behavior in and near the interaction regions, resulting from influences of the tunnel side-walls.
Author: Christopher Lockwood Rumsey
Publisher:
ISBN:
Category :
Languages : en
Pages : 29
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Book Description
Author: Giovanni Petrone
Publisher:
ISBN: 9788866185314
Category : Mathematics
Languages : en
Pages : 212
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Book Description
Author: Antony Jameson
Publisher: Cambridge University Press
ISBN: 1108837883
Category : Science
Languages : en
Pages : 627
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Book Description
Learn the design and analysis of numerical algorithms for aerodynamics. Ideal for graduates, researchers, and professionals in the field.
