Prediction and measurement of three-dimensional turbulent jets under suction and undercurrent flows in a maple-type test facility PDF Download
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Author: S. Y. Shim
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Languages : en
Pages : 0
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Author: S. Y. Shim
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Category :
Languages : en
Pages : 0
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Author: D. F. Myring
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Category : Turbulent boundary layer
Languages : en
Pages : 71
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722391102
Category :
Languages : en
Pages : 26
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A multigrid method is presented for the calculation of three-dimensional turbulent jets in crossflow. Turbulence closure is achieved with either the standard k-epsilon model or a Reynolds Stress Model (RSM). Multigrid acceleration enables convergence rates which are far superior to that for a single grid method. With the k-epsilon model the rate approaches that for laminar flow, but with RSM it is somewhat slower. The increased stiffness of the system of equations in the latter may be responsible. Computed results with both turbulence models are compared with experimental data for a pair of opposed jets in crossflow. Both models yield reasonable agreement with mean flow velocity but RSM yields better prediction of the Reynolds stresses. Demuren, A. O. Glenn Research Center NASA ORDER C-99066-G; RTOP 505-62-21...
Author: A. O. Demuren
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Category : Multigrid methods (Numerical analysis)
Languages : en
Pages : 28
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Author: G. J. Harloff
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Category :
Languages : en
Pages : 36
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Author: Harris J. Catrakis
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Category :
Languages : en
Pages :
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Author: V. Michelassi
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Category : Turbulence
Languages : en
Pages : 48
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721011148
Category :
Languages : en
Pages : 40
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The report presents an overview of jet noise computation utilizing the computational fluid dynamic solution of the turbulent jet flow field. The jet flow solution obtained with an appropriate turbulence model provides the turbulence characteristics needed for the computation of jet mixing noise. A brief account of turbulence models that are relevant for the jet noise computation is presented. The jet flow solutions that have been directly used to calculate jet noise are first reviewed. Then, the turbulent jet flow studies that compute the turbulence characteristics that may be used for noise calculations are summarized. In particular, flow solutions obtained with the k-e model, algebraic Reynolds stress model, and Reynolds stress transport equation model are reviewed. Since, the small scale jet mixing noise predictions can be improved by utilizing anisotropic turbulence characteristics, turbulence models that can provide the Reynolds stress components must now be considered for jet flow computations. In this regard, algebraic stress models and Reynolds stress transport models are good candidates. Reynolds stress transport models involve more modeling and computational effort and time compared to algebraic stress models. Hence, it is recommended that an algebraic Reynolds stress model (ASM) be implemented in flow solvers to compute the Reynolds stress components.Nallasamy, N.Glenn Research CenterTURBULENCE MODELS; AERODYNAMIC NOISE; COMPUTATIONAL FLUID DYNAMICS; JET AIRCRAFT NOISE; NOISE PREDICTION; FLOW DISTRIBUTION; TURBULENT JETS; REYNOLDS STRESS; STRESS ANALYSIS; MATHEMATICAL MODELS; ANISOTROPY
Author:
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ISBN:
Category :
Languages : en
Pages : 44
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781725571891
Category :
Languages : en
Pages : 32
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Incompressible three dimensional, turbulent boundary layer (3DTBL) experiments were simulated numerically by integrating the boundary layer equations together with an algebraic eddy viscosity turbulence model. For the flow treated, the downstream portion, where the crossflow was large, was not predicted with the present computational method; the flow was significantly influenced by elliptic flow field effects. Departures from the boundary layer concept are indicated. Calculations agreed reasonably well with the mean flow development up to separation. In one experiment the normal pressure gradients were found to be neligible in regions with large skewing and allowed testing turbulence models using the boundary layer equations. The simulation of this flow compared favorably with the experimental data throughout the flow field and suggested the applicability of algebraic eddy viscosity models for 3DTBLs. Mueller, U. R. Ames Research Center NASA-TM-84230, A-8873, NAS 1.15:84230 ...
