Supersonic Jet Exhaust Noise Investigation. Volume III. Computer User's Manual for Aero-Acoustic Predictions PDF Download
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Author: David R. Ferguson Publisher: ISBN: Category : Languages : en Pages : 683
Book Description
This report gives a detailed description of aerodynamic (Shock-free/Shocked flow) and acoustic turbulent mixing computer prediction programs developed by the General Electric Company for subsonic and supersonic simple exhaust jets. In addition to giving detailed descriptions of the aeroacoustic formulations and discussions of computer manual instructions for operating the program, extensive theory/data comparisons are given, as well as computer program listings and sample test cases. (Author).
Author: David R. Ferguson Publisher: ISBN: Category : Languages : en Pages : 683
Book Description
This report gives a detailed description of aerodynamic (Shock-free/Shocked flow) and acoustic turbulent mixing computer prediction programs developed by the General Electric Company for subsonic and supersonic simple exhaust jets. In addition to giving detailed descriptions of the aeroacoustic formulations and discussions of computer manual instructions for operating the program, extensive theory/data comparisons are given, as well as computer program listings and sample test cases. (Author).
Author: David R. Ferguson Publisher: ISBN: Category : Jet planes Languages : en Pages : 0
Book Description
This report gives a detailed description of aerodynamic (Shock-free/Shocked flow) and acoustic turbulent mixing computer prediction programs developed by the General Electric Company for subsonic and supersonic simple exhaust jets. In addition to giving detailed descriptions of the aeroacoustic formulations and discussions of computer manual instructions for operating the program, extensive theory/data comparisons are given, as well as computer program listings and sample test cases. (Author).
Author: Paul R. Knott Publisher: ISBN: Category : Languages : en Pages : 396
Book Description
This report discusses detailed accounts of major theoretical and experimental investigations directed toward obtaining better understanding and mathematical specification of supersonic turbulent jets. Complete theoretical discussions are given describing the influence of a jet's mean flow shrouding on acoustic radiation of heated and unheated jets, approximate closed form acoustic expressions for turbulent mixing noise characterized by self-noise and shear-noise are given, and theoretical aero-acoustic formulations for the orderly structure of supersonic jets are reviewed. Extensive theory/data comparisons of developed acoustic models are given. Experimental investigations aimed at studying high velocity jet refraction, and the influence of jet swirl and upstream combustion roughness on jet noise is presented. Additionally, an extensive series of laser velocimeter measurements for high velocity and high temperature simple circular jets is discussed. Results include hot-film/laser velocimeter comparisons for ambient jets, mean velocity and turbulent velocity plume surveys of heated supersonic shock-free and shocked flow nozzles, and a demonstration experiment illustrating the capability of performing in-jet turbulence to far-field acoustic cross-correlation. (Author).
Author: Paul R. Knott Publisher: ISBN: Category : Languages : en Pages : 137
Book Description
This report summarizes major theoretical aerodynamic and acoustic developments and experimental findings aimed at providing a better understanding and a detailed mathematical specification of the noise-producing sources of simple exhaust jets. A review is given of calculation procedures for shock wave structure and flow field properties of simple circular jets. Results of new theoretical acoustic developments illustrating the influence of a jet's mean flow shrouding on jet acoustic radiation for unheated and heated jets are outlined. Additional discussions of interesting insights regarding the classical turbulent mixing theory of jet noise and the aeroacoustic formulations for a jet's orderly structure are given. Summaries of a series of high velocity, high temperature velocity field measurements using a General Electric developed laser velocimeter are discussed, and the application of the velocimeter for performing turbulence spectra and in-jet to far-field cross-correlation type measurements is reviewed. Key experiments illustrating the influence of swirl and combustion roughness on jet noise generation/reduction are presented. Results of high velocity and high temperature refraction experiments are also discussed, as well as discussions concerning jet flow amplifying effects of injected low frequency noise. Additionally, suggestions concerning shock-related noise as related to full-size engines are given. And finally, recommendations for future investigations are given. (Author).
Author: Paul R. Knott Publisher: ISBN: Category : Languages : en Pages : 507
Book Description
This report is an acoustic data report presenting a series of parametric acoustic far-field and near-field results for subsonic and supersonic heated flow conditions for a simple conical nozzle (thin lip and thick lip) and a convergent-divergent nozzle at design and off-design conditions. (Author).
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781721010196 Category : Languages : en Pages : 90
Book Description
An empirical model to predict the effects of flight on the noise from a supersonic transport is developed. This model is based on an analysis of the exhaust jet noise from high subsonic flights of the F-15 ACTIVE Aircraft. Acoustic comparisons previously attainable only in a wind tunnel were accomplished through the control of both flight operations and exhaust nozzle exit diameter. Independent parametric variations of both flight and exhaust jet Mach numbers at given supersonic nozzle pressure ratios enabled excellent correlations to be made for both jet broadband shock noise and jet mixing noise at flight speeds up to Mach 0.8. Shock noise correlated with flight speed and emission angle through a Doppler factor exponent of about 2.6. Mixing noise at all downstream angles was found to correlate well with a jet relative velocity exponent of about 7.3, with deviations from this behavior only at supersonic eddy convection speeds and at very high flight Mach numbers. The acoustic database from the flight test is also provided.Norum, Thomas D. and Garber, Donald P. and Golub, Robert A. and Santa Maria, Odilyn L. and Orme, John S.Armstrong Flight Research Center; Langley Research CenterJET AIRCRAFT NOISE; JET EXHAUST; SUBSONIC SPEED; SUPERSONIC SPEED; MATHEMATICAL MODELS; AEROACOUSTICS; FLIGHT TESTS; SHOCK WAVES; SUPERSONIC TRANSPORTS; MACH NUMBER; JET MIXING FLOW; F-15 AIRCRAFT; PRESSURE RATIO; EXHAUST NOZZLES; VORTICES; DATA REDUCTION; DATA ACQUISITION
Author: Robert Golub Publisher: BiblioGov ISBN: 9781289264161 Category : Languages : en Pages : 210
Book Description
This report describes a computer program, HSRNOISE, that predicts noise levels for a supersonic aircraft powered by mixed flow turbofan engines with rectangular mixer-ejector nozzles. It fully documents the noise prediction algorithms, provides instructions for executing the HSRNOISE code, and provides predicted noise levels for the High Speed Research (HSR) program Technology Concept (TC) aircraft. The component source noise prediction algorithms were developed jointly by Boeing, General Electric Aircraft Engines (GEAE), NASA and Pratt & Whitney during the course of the NASA HSR program. Modern Technologies Corporation developed an alternative mixer ejector jet noise prediction method under contract to GEAE that has also been incorporated into the HSRNOISE prediction code. Algorithms for determining propagation effects and calculating noise metrics were taken from the NASA Aircraft Noise Prediction Program.
Author: David R. Ferguson
Author: David R. Ferguson
Author: David R. Ferguson
Author: Lockheed-Georgia Company
Author: Paul R. Knott
Author: 
Author: Paul R. Knott
Author: Paul R. Knott
Author: 
Author: National Aeronautics and Space Administration (NASA)
Author: Robert Golub