Flow field and acoustic properties of a Mach number 0·9 jet at a low Reynolds number

Stromberg, J.L.; McLaughlin, Dennis K.; Troutt, T. R.

doi:10.1016/0022-460x(80)90650-1

Cited by 194 publications

(41 citation statements)

References 27 publications

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“…Compared to measurements provided by Mollo-Christensen et al, 32 Lush, 77 and Bogey et al 78 for Mach number 0.9 jets at Reynolds numbers higher than Re D = 5 × 10 5 , they are found to be higher for all radiation angles. They however decrease with Re D , which is not surprising given the lowering of peak turbulence intensities in Figure 11, reducing the gap with 31,42,46 at Re D ≤ 10 4 and mixing layers 47 at Re θ ≤ 500, noise reduction arose in a few experiments on circular jets at moderate Reynolds numbers as in this study. This trend was, for instance, identified by Viswanathan 36 for hot jets at Re D ≤ 4 × 10 5 .…”

Section: Acoustic Fieldssupporting

confidence: 69%

“…For subsonic jets, some similarities remain between the sound fields of low and high Reynolds number jets as shown by the data of Stromberg et al 31 for a Mach number 0.9 jet at Re D = 3.6 × 10 3 . It is however well known that the spectral properties of subsonic jet noise vary with the Reynolds number below a threshold value between Re D = 10 5 and Re D = 4 × 10 5 according to authors such as Yamamoto and Arndt, 33 Long and Arndt, 34 Bridges and Hussain, 35 and Viswanathan.…”

Section: Introductionmentioning

confidence: 68%

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Effects of moderate Reynolds numbers on subsonic round jets with highly disturbed nozzle-exit boundary layers

2012

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Particle transport in a turbulent boundary layer: Non-local closures for particle dispersion tensors accounting for particle-wall interactions Phys. Fluids 24, 103304 (2012) Convection and reaction in a diffusive boundary layer in a porous medium: Nonlinear dynamics Chaos 22, 037113 (2012) Symmetry analysis and self-similar forms of fluid flow and heat-mass transfer in turbulent boundary layer flow of a nanofluid Phys. Fluids 24, 092003 (2012) Detuned resonances of Tollmien-Schlichting waves in an airfoil boundary layer: Experiment, theory, and direct numerical simulation Phys. Fluids 24, 094103 (2012) Additional information on Phys. FluidsThe effects of moderate Reynolds numbers on the flow and acoustic fields of initially highly disturbed isothermal round jets at Mach number M = 0.9 and diameter-based Reynolds numbers Re D between 2.5 × 10 4 and 2 × 10 5 are investigated using largeeddy simulation under carefully controlled conditions. To the best of our knowledge, this is the first comprehensive study of its kind. The jets originate at z = 0 from a pipe nozzle of radius r 0 , in which a tripping procedure is applied to the boundary layers. At the nozzle exit, laminar-like mean velocity profiles of thickness δ 0.15r 0 and momentum thickness δ θ 0.018r 0 , yielding Reynolds numbers Re θ varying from 256 to 1856 depending on Re D , and peak turbulence intensities around 9% of the jet velocity, are thus obtained. As the Reynolds number increases, the mixing layers develop more slowly, with smaller integral length scales and lower levels of velocity fluctuations. The axial profiles of turbulence intensities become smoother, showing a clear overshoot around z = 2r 0 at Re D = 2.5 × 10 4 , but a monotonical growth at Re D = 2 × 10 5 . Velocity spectra downstream of the nozzle exit also broaden with Re D , as expected. Large-scale components usually observed in turbulent boundary layers and shear layers, characterized by Strouhal numbers St θ 0.013 around z = r 0 and by azimuthal spacings λ θ δ, remain dominant, although the contribution of fine-scale structures with λ θ ≤ δ/2 strengthens. Moreover, with rising Re D , the jet potential core lengthens slightly, but the flow properties do not change significantly farther downstream. Finally, lower sound pressure levels are generated, with a decrease of about 2 dB over the range of Re D considered. C 2012 American Institute of Physics.

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Section: Acoustic Fieldssupporting

confidence: 69%

Section: Introductionmentioning

confidence: 68%

Effects of moderate Reynolds numbers on subsonic round jets with highly disturbed nozzle-exit boundary layers

2012

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“…13. In follow-on work UCLA undertook the study of a M=0.9 jet whose experimental conditions match the experiments of Stromberg et al (1980). These computations follow similar but considerably simpler methods using the Euler equations that have been ongoing at NASA Glenn Research Center for some time: e.g., Hixon et al (1997).…”

Section: Numerical Simulationsmentioning

confidence: 99%

Highlights of Aeroacoustics Research in the U.S.—1998

Raman

McLaughlin

1999

Journal of Sound and Vibration

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“…Therefore, numerical simulation of the jet flows process at large Reynolds numbers and the determination of acoustic disturbances generated by them presents considerable computational difficulties. In turn, the flow parameters of the jets with low Reynolds numbers are well studied [1][2][3] and can be used to validate the numerical method and schemes, since there is no need to use a very detailed grid and additional assumptions, related with different turbulence models.…”

Section: Introductionmentioning

confidence: 99%

“…To determine acoustic disturbances, we use the Ffowcs Williams and Hawkings analogy, which is implemented in the libAcoustic library based on the OpenFOAM package [9,10]. The flow parameters and geometry match an experimental study conducted by Stromberg et al [1] and results are compared to their data whenever possible.…”

Section: Introductionmentioning

confidence: 99%

The numerical simulation of compressible jet at low Reynolds number using OpenFOAM

2019

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The paper presents an analysis of various approaches for calculation gas-dynamic parameters and acoustic perturbations generated by a compressible jet at low Reynolds number (M = 0.9, Re = 3600). The jet flow parameters at selected conditions are well studied and can be used for validation of the numerical methods and schemes. The OpenFOAM software package with various approaches (solvers) such as pimpleCentralFoam, dbnsTurbFoam and new QGDFoam solver based on QGD-algorithms are considered. The results of time-averaged flow parameters and acoustic properties are compared with the experimental data. To determine the acoustic perturbation the Ffowcs Williams and Hawkings analogy implemented in our OpenFOAM library (libAcoustic) has been used.

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Flow field and acoustic properties of a Mach number 0·9 jet at a low Reynolds number

Cited by 194 publications

References 27 publications

Effects of moderate Reynolds numbers on subsonic round jets with highly disturbed nozzle-exit boundary layers

Effects of moderate Reynolds numbers on subsonic round jets with highly disturbed nozzle-exit boundary layers

Highlights of Aeroacoustics Research in the U.S.—1998

The numerical simulation of compressible jet at low Reynolds number using OpenFOAM

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