The Effect of Velocity Profiles on Supersonic Jet Noise PDF Download
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Author: T. R. S. Bhat
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: T. R. S. Bhat
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781728712550
Category : Science
Languages : en
Pages : 40
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The effect of velocity profiles on supersonic jet noise are studied by using stability calculations made for a shock-free coannular jet, with both the inner and outer flows supersonic. The Mach wave emission process is modeled as the noise generated by the large scale turbulent structures or the instability waves in the mixing region. Both the vortex-sheet and the realistic finite thickness shear layer models are considered. The stability calculations were performed for both inverted and normal velocity profiles. Comparisons are made with the results for an equivalent single jet, based on equal thrust, mass flow rate and exit area to that of the coannular jet. The advantages and disadvantages of these velocity profiles as far as noise radiation is concerned are discussed. It is shown that the Rayleigh's model prediction of the merits and demerits of different velocity profiles are in good agreement with the experimental data. Tiwari, S. N. and Bhat, T. R. S. Unspecified Center NAG1-1581
Author: E. J. Richards
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722189334
Category :
Languages : en
Pages : 30
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An improved version of a previously validated linearized Euler equation solver is used to compute the noise generated by coannular supersonic jets. Results for a single supersonic jet are compared to the results from both a normal velocity profile and an inverted velocity profile supersonic jet. Hixon, R. and Shih, S.-H. and Mankbadi, Reda R. Glenn Research Center NCC3-531; RTOP 523-36-13...
Author:
Publisher:
ISBN:
Category : Jet planes
Languages : en
Pages : 194
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723430411
Category :
Languages : en
Pages : 184
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Instability waves have been established as the dominant source of mixing noise radiating into the downstream arc of a supersonic jet when the waves have phase velocities that are supersonic relative to ambient conditions. Recent theories for supersonic jet noise have used the concepts of growing and decaying linear instability waves for predicting radiated noise. This analysis is extended to the prediction of noise radiation from supersonic coaxial jets. Since the analysis requires a known mean flow and the coaxial jet mean flow is not described easily in terms of analytic functions, a numerical prediction is made for its development. The Reynolds averaged, compressible, boundary layer equations are solved using a mixing length turbulence model. Empirical correlations are developed for the effects of velocity and temperature ratios and Mach number. Both normal and inverted velocity profile coaxial jets are considered. Comparisons with measurements for both single and coaxial jets show good agreement. The results from mean flow and stability calculations are used to predict the noise radiation from coaxial jets with different operating conditions. Comparisons are made between different coaxial jets and a single equivalent jet with the same total thrust, mass flow, and exit area. Results indicate that normal velocity profile jets can have noise reductions compared to the single equivalent jet. No noise reductions are found for inverted velocity profile jets operated at the minimum noise condition compared to the single equivalent jet. However, it is inferred that changes in area ratio may provide noise reduction benefits for inverted velocity profile jets. Dahl, Milo D. Glenn Research Center AEROACOUSTICS; COAXIAL FLOW; GAS JETS; JET AIRCRAFT NOISE; NOISE PREDICTION (AIRCRAFT); NOISE REDUCTION; SUPERSONIC JET FLOW; COMPUTATIONAL FLUID DYNAMICS; FLOW STABILITY; MACH NUMBER; MIXING LENGTH FLOW THEORY; TEMPERATURE RATIO; VELOCITY DISTRIBUTION...
Author: J. B. Ollerhead
Publisher:
ISBN:
Category : Noise
Languages : en
Pages : 116
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Author: Lockheed-Georgia Company
Publisher:
ISBN:
Category : Jet planes
Languages : en
Pages : 270
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Author: Jay C. Hardin
Publisher:
ISBN:
Category : Aerodynamic noise
Languages : en
Pages : 36
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Author: Kostas Psilakos
Publisher:
ISBN:
Category :
Languages : en
Pages : 213
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