Azimuthal Structure of Low-Frequency Noise of Installed Jet

Faranosov, G. A.; Belyaev, I. V.; Kopiev, V. F.; Bychkov, O. P.

doi:10.2514/1.j057476

Cited by 14 publications

(12 citation statements)

References 43 publications

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“…The main idea of the control of the low-frequency installation noise is based on the assumption about the dominant role of instability waves in the process of noise generation. 6,[9][10][11][13][14][15][16][17] It was shown 6,14,15 that if the trailing edge of the wing lies in the irrotational near field of the jet, the problem of the low-frequency installation noise modeling can be solved in a linear framework. Namely, for each frequency, there is a linear transfer function between the near-field hydrodynamic pulsations of the jet, considered as if the plate is absent, and the far-field sound caused by the scattering of these pulsations on the trailing edge:…”

Section: Control Strategymentioning

confidence: 99%

“…The position of the plate relative to the jet was chosen from the following considerations. As has been mentioned above, in most of the recent publications, 5,6,[9][10][11][13][14][15][16][17] jet-wing installation noise was studied for the case when the trailing edge lies in the linear hydrodynamic region of the jet near-field. In practice, such conditions may be realized for jetunder-the-wing configurations with not very large flap deflection angles.…”

Section: A Experimental Setupmentioning

confidence: 99%

“…12 This allowed developing simple models, in which the field interacting with the plate trailing edge is modeled by the superposition of the near-field evanescent waves of different azimuthal numbers as if the plate is absent. 6,10,11,[13][14][15][16][17] In the current study, we are also focused on the configuration when the plate is not intruded into the jet shear layer so that linear mechanism of low-frequency installation noise is valid.…”

Section: A Experimental Setupmentioning

confidence: 99%

“…Particularly, at low and moderate frequencies, it may cause the occurrence of an additional efficient noise source associated with the interaction between the hydrodynamic near field of the jet and the wing trailing edge. [5][6][7][8][9][10][11][12][13][14][15][16][17] To reduce jet-wing installation noise, several approaches can be used. Most popular methods are related to the modifications of nozzle-wing geometry: nozzle modifications or wing/flaps modifications.…”

Section: Introductionmentioning

confidence: 99%

“…While the problem of active control of free (uninstalled) jet noise has a rich background, [18][19][20][21][22][23][24][25][26][27][28][29][30] installed jet noise, to our knowledge, has not been considered from this point of view. Recent studies 5,6,[9][10][11][13][14][15][16][17] have revealed that significant noise intensification at low and moderate frequencies observed for installed jets is related to the scattering of the jet near-field pressure pulsations on the wing trailing edge. This pressure field is associated with instability waves developing in the jet shear layer.…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

Plasma-based active closed-loop control of instability waves in unexcited turbulent jet. Part 2. Installed jet.

Faranosov¹,

Kopiev²,

Bychkov³

et al. 2019

25th AIAA/CEAS Aeroacoustics Conference

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The paper considers the possibility of controlling jet-wing interaction noise based on the results obtained for free jet in the Part I of the study. 1 The main idea is connected with the control of the amplitude of wave packets developing in a turbulent jet. The presence of a wing makes diffraction of the jet near-field pulsations an effective sound source in case of close location of the jet shear layer and the wing trailing edge. Therefore, a decrease in the intensity of wave packets can lead to noise reduction in the far field of the installed jet. In the current work it is shown, for the first time, that active closed-loop control system using high frequency dielectric barrier discharge (HF DBD) plasma actuator can lead to a reduction of pressure pulsations not only in the near-field but also in the far acoustic field of the jet. Initially, the effect of the installation noise reduction is demonstrated for an excited jet. Then, the possibility of noise reduction of unexcited installed jet is shown. The location of the actuator on the edge, the required energy input, and the robustness of the control system itself are quite promising in terms of noise reduction of realistic jet-wing configurations.

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Section: Control Strategymentioning

confidence: 99%

Section: A Experimental Setupmentioning

confidence: 99%

Section: A Experimental Setupmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Plasma-based active closed-loop control of instability waves in unexcited turbulent jet. Part 2. Installed jet.

Faranosov¹,

Kopiev²,

Bychkov³

et al. 2019

25th AIAA/CEAS Aeroacoustics Conference

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Problems of a Supersonic Business Aircraft Design with Regard to Cabin Noise Requirements

Moshkov¹,

Strelets²

2023

Springer Aerospace Technology

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Investigation into the turbulence statistics of installed jets using hot-wire anemometry

2020

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This work presents a detailed study of the turbulence flow statistics of a jet mounted with its axis parallel to a rigid flat plate. Hot-wire constant temperature anemometry has been used to measure the single-point and two-point statistics of the axial velocity component at several locations within the jet flow field. Results show that the jet mean flow near the plate surface is subjected to a local acceleration and redirection due to a Coandă-type effect. The propagation of these effects downstream of the plate trailing edge is strongly dependent on the plate position. Regarding the velocity fluctuations, the mean turbulence intensity levels are seen to decrease as the radial distance between the jet and surface decreases. Analysis of the single-point power spectral density data on the shear layer close to the plate shows that the reduction in magnitude of the low-frequency content of the energy spectrum is responsible for the decrease in turbulence intensity. Additionally, the characteristic time and length scales computed from two-point measurements reduce as the plate is mounted closer to the jet centre-line. The axial eddy convection velocity is seen to increase in the region of high turbulent kinetic energy in the shear layer adjacent to the surface. Empirical models for turbulence characteristic scales and eddy convection velocity are presented. These findings suggest that both the amplitude and distribution of the jet mixing noise sources are affected when closely installed next to a surface. This paper is a continuation of a recent investigation on the turbulence statistics of isolated jets presented in Proença (Exp Fluids 60(4):63, 2019). Graphic abstract

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Azimuthal Structure of Low-Frequency Noise of Installed Jet

Cited by 14 publications

References 43 publications

Plasma-based active closed-loop control of instability waves in unexcited turbulent jet. Part 2. Installed jet.

Plasma-based active closed-loop control of instability waves in unexcited turbulent jet. Part 2. Installed jet.

Problems of a Supersonic Business Aircraft Design with Regard to Cabin Noise Requirements

Investigation into the turbulence statistics of installed jets using hot-wire anemometry

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