Turbulence Modeling ; Turbulence Compressibility Corrections ; Three-dimensional Navier-Stokes Method with Two-equation Turbulence Models for Efficient Numerical Simulation of Hypersonic Flows ; Three-dimensional Navier-Stokes Simulations with Two-equation Turbulence Models of Intersecting Shock-waves/turbulent Boundary Layer at Mach 8.3 PDF Download
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Author: Jorge E. Bardina
Publisher:
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Category :
Languages : en
Pages :
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Author: Jorge E. Bardina
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Category : Fluid mechanics
Languages : en
Pages : 46
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Category : Aeronautics
Languages : en
Pages : 548
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Category : Aeronautics
Languages : en
Pages : 1572
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Category : Mechanics, Applied
Languages : en
Pages : 400
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Category : Aeronautics
Languages : en
Pages : 934
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Category : Aeronautics
Languages : en
Pages : 712
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A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722849597
Category :
Languages : en
Pages : 100
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The primary objective of this work is to provide accurate numerical solutions for selected flow fields and to compare and evaluate the performance of selected turbulence models with experimental results. Four popular turbulence models have been tested and validated against experimental data often turbulent flows. The models are: (1) the two-equation k-epsilon model of Wilcox, (2) the two-equation k-epsilon model of Launder and Sharma, (3) the two-equation k-omega/k-epsilon SST model of Menter, and (4) the one-equation model of Spalart and Allmaras. The flows investigated are five free shear flows consisting of a mixing layer, a round jet, a plane jet, a plane wake, and a compressible mixing layer; and five boundary layer flows consisting of an incompressible flat plate, a Mach 5 adiabatic flat plate, a separated boundary layer, an axisymmetric shock-wave/boundary layer interaction, and an RAE 2822 transonic airfoil. The experimental data for these flows are well established and have been extensively used in model developments. The results are shown in the following four sections: Part A describes the equations of motion and boundary conditions; Part B describes the model equations, constants, parameters, boundary conditions, and numerical implementation; and Parts C and D describe the experimental data and the performance of the models in the free-shear flows and the boundary layer flows, respectively. Bardina, J. E. and Huang, P. G. and Coakley, T. J. Ames Research Center...
Author: Gregory Allan Ashford
Publisher:
ISBN:
Category :
Languages : en
Pages : 500
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Author:
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Category :
Languages : en
Pages : 648
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