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Author: Ian Stanley Ferguson Jones
Publisher:
ISBN:
Category : Jet plane sounds
Languages : en
Pages : 60
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Book Description
Author: Ian Stanley Ferguson Jones
Publisher:
ISBN:
Category : Jet plane sounds
Languages : en
Pages : 60
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
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Book Description
Author: Christophe Brun
Publisher: Springer Science & Business Media
ISBN: 3540899561
Category : Technology & Engineering
Languages : en
Pages : 344
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Book Description
Large Eddy Simulation (LES) is a high-fidelity approach to the numerical simulation of turbulent flows. Recent developments have shown LES to be able to predict aerodynamic noise generation and propagation as well as the turbulent flow, by means of either a hybrid or a direct approach. This book is based on the results of two French/German research groups working on LES simulations in complex geometries and noise generation in turbulent flows. The results provide insights into modern prediction approaches for turbulent flows and noise generation mechanisms as well as their use for novel noise reduction concepts.
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781723765001
Category : Science
Languages : en
Pages : 42
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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:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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Book Description
Author: Arnold Goldburg
Publisher:
ISBN:
Category : Aerodynamic noise
Languages : en
Pages : 140
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781720664826
Category :
Languages : en
Pages : 48
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Book Description
The model-based approach, used by the JeNo code to predict jet noise spectral directivity, is described. A linearized form of Lilley's equation governs the non-causal Green s function of interest, with the non-linear terms on the right hand side identified as the source. A Reynolds-averaged Navier-Stokes (RANS) solution yields the required mean flow for the solution of the propagation Green s function in a locally parallel flow. The RANS solution also produces time- and length-scales needed to model the non-compact source, the turbulent velocity correlation tensor, with exponential temporal and spatial functions. It is shown that while an exact non-causal Green s function accurately predicts the observed shift in the location of the spectrum peak with angle as well as the angularity of sound at low to moderate Mach numbers, the polar directivity of radiated sound is not entirely captured by this Green s function at high subsonic and supersonic acoustic Mach numbers. Results presented for unheated jets in the Mach number range of 0.51 to 1.8 suggest that near the peak radiation angle of high-speed jets, a different source/Green s function convolution integral may be required in order to capture the peak observed directivity of jet noise. A sample Mach 0.90 heated jet is also discussed that highlights the requirements for a comprehensive jet noise prediction model.Khavaran, Abbas and Bridges, James and Georgiadis, NicholasGlenn Research CenterNOISE PREDICTION; TURBULENCE; JET AIRCRAFT NOISE; CONVOLUTION INTEGRALS; EXPONENTIAL FUNCTIONS; MACH NUMBER; MATHEMATICAL MODELS; SUPERSONIC SPEED
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1352
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Book Description
Author: Ira R. Schwartz
Publisher:
ISBN:
Category : Aerodynamic noise
Languages : en
Pages : 548
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 64
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Book Description
