Prediction of fluid flow and acoustic field of a supersonic jet using vorticity confinement

2018 ◽  
Vol 144 (3) ◽  
pp. 1521-1527
Author(s):  
M. Sadri ◽  
K. Hejranfar ◽  
M. Ebrahimi
Keyword(s):  
Fluid Flow ◽  
Acoustic Field ◽  
Supersonic Jet ◽  
Vorticity Confinement

A Numerical Study on Fluid Flow and Acoustic Characteristics of a Supersonic Impinging Jet Using Vorticity Confinement

2019 ◽  
Vol 105 (6) ◽  
pp. 1127-1136
Author(s):  
M. Sadri ◽  
K. Hejranfar ◽  
M. Ebrahimi
Keyword(s):  
Fluid Flow ◽  
Finite Difference ◽  
Difference Scheme ◽  
Acoustic Field ◽  
Finite Difference Scheme ◽  
High Order ◽  
Compact Finite Difference Scheme ◽  
Compact Finite Difference ◽  
Vorticity Confinement ◽  
Supersonic Impinging Jet

The objective of this work is to numerically study the fluid flow and acoustic field of a supersonic impinging jet by applying the vorticity confinement (VC) method. For this aim, the three-dimensional compressible Navier-Stokes equations with the incorporation of the VC method are considered and the resulting system of equations is solved by using the sixth-order compact finite-difference scheme. To eliminate the numerical instability, a low-pass high-order filter is used. The nonreflective boundary conditions are applied for all the free boundaries and the radiated sound field is obtained by the Kirchhoff surface integration. Comparisons of the present results with the experimental data and other numerical simulations show that the solution methodology adopted based on the application of the VC method with the high-order compact finite-difference scheme provides a good prediction of the fluid flow and the acoustic field of the impingement region on coarser grids than that usually required in the LESs, and thus, the calculations of coarse grid LESs are improved.

CALCULATION OF THE INTEGRAL NOISE LEVEL AT A FIELD POINT OF A FREE SUPERSONIC JET OF A ROCKET ENGINE

Akustika ◽  
2020 ◽  
Vol 36 (36) ◽  
pp. 22-24
Author(s):  
Anatoly Kochergin ◽  
Valeeva Ksenia
Keyword(s):  
Acoustic Field ◽  
Noise Level ◽  
Rocket Engine ◽  
Supersonic Jet ◽  
Noise Sources ◽  
Field Point

The paper considers an acoustic field created by a supersonic jet (CES) of a rocket engine freely flowing into flooded space. The acoustic field was presented in the form of a diagram of noise isobars, from which it can be seen that the acoustic field is formed by two effective noise sources: the nearest one, lying at a distance of 5-10 calibers from the nozzle cut and the far one, lying at a distance of 15-30 calibers from the nozzle cut.

Numerical Prediction of an Acoustic Field of a Supersonic Jet Impinging on a Plate at Different Inclination Angles

2014 ◽  
Author(s):  
Vladimir Golubev ◽  
Anstasios Lyrintzis ◽  
Reda R. Mankbadi ◽  
Konstantin A. Kurbatskii ◽  
Barrett Guenthoer
Keyword(s):  
Acoustic Field ◽  
Supersonic Jet ◽  
Numerical Prediction ◽  
Inclination Angles

Numerical analysis of the interaction between fluid flow and acoustic field at the mouth-opening of a flue instrument

2013 ◽  
Vol 133 (5) ◽  
pp. 3321-3321
Author(s):  
Takahiro Akamura ◽  
Yuki Nagao ◽  
Takuya Iwasaki ◽  
Ken'ichiro Nakano ◽  
Kin'ya Takahashi ◽  
...  
Keyword(s):  
Fluid Flow ◽  
Numerical Analysis ◽  
Acoustic Field ◽  
Mouth Opening

Acoustic field of a shielded rectangular supersonic jet

2015 ◽  
Vol 138 (3) ◽  
pp. 1915-1915
Author(s):  
Ephraim Gutmark ◽  
Pablo Mora ◽  
Florian Baier
Keyword(s):  
Acoustic Field ◽  
Supersonic Jet

Acoustics measurements of military-style supersonic beveled nozzle jets with interior corrugations

2016 ◽  
Vol 16 (1-2) ◽  
pp. 21-43 ◽  
Author(s):  
Russell W Powers ◽  
Dennis K McLaughlin
Keyword(s):  
Noise Reduction ◽  
Acoustic Field ◽  
High Speed ◽  
Supersonic Jet ◽  
Jet Noise ◽  
Operating Conditions ◽  
Military Aircraft ◽  
Azimuthal Dependence ◽  
Penn State ◽  
Mixing Noise

Increasingly powerful and noisy military aircraft have generated the need for research leading to the development of supersonic jet noise reduction devices. The hot, high speed supersonic jets exhausting from military aircraft during takeoff present a most challenging problem. The present study extends prior research on two methods of noise reduction. The first is the internal nozzle corrugations pioneered by Seiner et al. and the second is the beveled exit plane explored most recently by Viswanathan. A novel research idea of creating fluidic corrugations similar to the nozzle corrugations has been initiated by Penn State. To further the understanding and analysis of the fluidic corrugations, the present study focuses on the flow field and acoustic field of nozzles with two, three, and six conventional, hardwalled corrugations. The effect of the combination of the internal corrugations with a beveled nozzle is explored. The results show that significant noise reductions of over 3 dB of the mixing noise and the broadband shock-associated noise can be achieved. The combination of the beveled nozzle and the internal nozzle corrugations showed that there is less azimuthal dependence of the acoustic field than for the purely beveled nozzle. The combination nozzle was shown to reduce the noise over a wider range of polar angles and operating conditions than either the purely beveled nozzle or the purely corrugated nozzle.

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