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Author: Chan M. Kim
Publisher:
ISBN:
Category :
Languages : en
Pages : 14
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Author: Chan M. Kim
Publisher:
ISBN:
Category :
Languages : en
Pages : 14
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Author: Bulent Imamoglu
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 154
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Author: Kalyan Goparaju
Publisher:
ISBN:
Category : Aerospace engineering
Languages : en
Pages : 174
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Jet noise has been a major source of concern for commercial and military aviation sectors alike. The need to assuage the adverse impact of jet noise on human health has led to increased interest in jet noise source identification and noise level minimization/mitigation. Most previous works on common round supersonic jets have primarily explored the ideal case of simple, perfectly expanded jet configurations. In real world scenarios however, many of these simplifications do not hold. Two such considerations are examined in this work. The first is a simple configuration operating at complex operating conditions, specifically an imperfect expansion i.e. where the jets are operating at off-design conditions. The second concerns a complex configuration at simple conditions: specifically two jets (twin-jets such as those on fighter aircraft) operating in close proximity to each other. In this work, Large Eddy Simulation (LES) based high-fidelity computations are used to understand the dynamics of imperfectly expanded and twin-jets respectively, with the following objectives: 1) Identify the impact of active flow control techniques on the plume dynamics and acoustic characteristics of underexpanded jets, and 2) Investigate the interaction dynamics of the twin-jet plumes and study its associated sound field which exhibits complex radiation characteristics.
Author: Gibin Raju
Publisher: GRIN Verlag
ISBN: 366876137X
Category : Technology & Engineering
Languages : en
Pages : 95
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Master's Thesis from the year 2018 in the subject Engineering - Aerospace Technology, grade: 3.64, University of Cincinnati, language: English, abstract: The aim of this thesis is to discuss the vital role of shock-cell and Mach disk in noise production of jet engines. This study focuses on calculation of shock-cell spacing and Mach disk from various configuration of C-D Nozzles using Shadowgraph technique and detailing on how it varies with the test conditions. In the past three decades, the air traffic has nearly increased by about 40% and have always called for alternative propulsion techniques to replace or support the current traditional propulsion methodology in order to travel longer distances in shorter frame of time. In the light of current demand, the thesis draws motivation from increase in noise levels due to technological advancements of meeting higher specific thrust thus, achieving higher efficiency. The thesis emphasizes on the study of shock-cell noise by developing a complete view of the shock-cell structure and associated parameters with an imperfectly expanded supersonic jet on CD Nozzles over range of under-expanded, design and over-expanded operating conditions. In the entire thesis study, the heated jets from the different C-D Nozzle are analyzed for proper visualization for the shock-cell structure. Shadowgraph is used in current study as it offers very high flexibility and acts as an excellent technique for visualizing the shock diamond exhaust structure and turbulent eddies. A systematic analysis has been performed to quantify the shadowgraph data through semantic video analysis and measured the shock-cell spacing over different temperature ratios (TR) and nozzle pressure ratios (NPR). Circular, rectangular and method of characteristics (MOC) convergent-divergent nozzles of 1.5 design Mach number with and without plates were tested to interpret the results. The data recorded during the experiment was processed to obtain an averaged image. Further, the averaged images were utilized to compute the shock-cell spacing of each nozzle. The computed shock-cell spacing is compared over the theoretical shock-cell length using empirical formula to validate the results. A good match has been established between theoretical and experimental results for the tested nozzles expect for over-expanded operating conditions.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 492
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Author: Ching Y. Loh
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Nasa Technical Reports Server (Ntrs)
Publisher: BiblioGov
ISBN: 9781289236328
Category :
Languages : en
Pages : 84
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Codes for predicting supersonic jet mixing and broadband shock-associated noise were assessed using a database containing noise measurements of a jet issuing from a convergent nozzle. Two types of codes were used to make predictions. Fast running codes containing empirical models were used to compute both the mixing noise component and the shock-associated noise component of the jet noise spectrum. One Reynolds-averaged, Navier-Stokes-based code was used to compute only the shock-associated noise. To enable the comparisons of the predicted component spectra with data, the measured total jet noise spectra were separated into mixing noise and shock-associated noise components. Comparisons were made for 1/3-octave spectra and some power spectral densities using data from jets operating at 24 conditions covering essentially 6 fully expanded Mach numbers with 4 total temperature ratios.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721276707
Category :
Languages : en
Pages : 26
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An acoustic prediction capability for supersonic axisymmetric jets was developed on the basis of OVERFLOW Navier-Stokes CFD (Computational Fluid Dynamics) code of NASA Langley Research Center. Reynolds-averaged turbulent stresses in the flow field are modeled with the aid of Spalart-Allmaras one-equation turbulence model. Appropriate acoustic and outflow boundary conditions were implemented to compute time-dependent acoustic pressure in the nonlinear source-field. Based on the specification of acoustic pressure, its temporal and normal derivatives on the Kirchhoff surface, the near-field and the far-field sound pressure levels are computed via Kirchhoff surface integral, with the Kirchhoff surface chosen to enclose the nonlinear sound source region described by the CFD code. The methods are validated by a comparison of the predictions of sound pressure levels with the available data for an axisymmetric turbulent supersonic (Mach 2) perfectly expanded jet. Kandula, Max and Caimi, Raoul and Steinrock, T. (Technical Monitor) Kennedy Space Center NASA/TM-2001-210263, NAS 1.15:210263
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781719493345
Category :
Languages : en
Pages : 78
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Codes for predicting supersonic jet mixing and broadband shock-associated noise were assessed using a database containing noise measurements of a jet issuing from a convergent nozzle. Two types of codes were used to make predictions. Fast running codes containing empirical models were used to compute both the mixing noise component and the shock-associated noise component of the jet noise spectrum. One Reynolds-averaged, Navier-Stokes-based code was used to compute only the shock-associated noise. To enable the comparisons of the predicted component spectra with data, the measured total jet noise spectra were separated into mixing noise and shock-associated noise components. Comparisons were made for 1/3-octave spectra and some power spectral densities using data from jets operating at 24 conditions covering essentially 6 fully expanded Mach numbers with 4 total temperature ratios. Dahl, Milo D. Glenn Research Center JET MIXING FLOW; JET AIRCRAFT NOISE; SUPERSONIC JET FLOW; AERODYNAMIC NOISE; NOISE MEASUREMENT; NOISE SPECTRA; FLUID JETS; MACH NUMBER; PREDICTIONS; SHOCK WAVES; TEMPERATURE RATIO
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
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