Analysis of aeroacoustic characteristics of a supersonic jet at designed conditions based on numerical simulation

Мұқаба

Дәйексөз келтіру

Толық мәтін

Ашық рұқсат Ашық рұқсат
Рұқсат жабық Рұқсат берілді
Рұқсат жабық Тек жазылушылар үшін

Аннотация

The work is devoted to the numerical simulation of aeroacoustic characteristics of a supersonic jet issuing from a Laval nozzle at the design Mach number M=2. The results of the large-eddy simulations (LES) are presented. Characteristics of mean jet flow and its fluctuations, as well as the characteristics of the far-field jet noise, including its azimuthal content, are obtained. The results of the simulation are compared with experimental data and their acceptable agreement is shown. It is concluded that there are various noise generation mechanisms in the considered jet.

Толық мәтін

Рұқсат жабық

Авторлар туралы

O. Bychkov

FAI TsAGI, Research Moscow Complex TsAGI

Email: georgefalt@rambler.ru
Ресей, Moscow

I. Mironyuk

FAI TsAGI, Research Moscow Complex TsAGI

Email: georgefalt@rambler.ru
Ресей, Moscow

I. Solntsev

FAI TsAGI, Research Moscow Complex TsAGI

Email: georgefalt@rambler.ru
Ресей, Moscow

G. Faranosov

FAI TsAGI, Research Moscow Complex TsAGI

Хат алмасуға жауапты Автор.
Email: georgefalt@rambler.ru
Ресей, Moscow

M. Yudin

FAI TsAGI, Research Moscow Complex TsAGI

Email: georgefalt@rambler.ru
Ресей, Moscow

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Әрекет
1. JATS XML
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2. Fig. 1. (a) — Laval nozzle tested in [4]; (b) — calculated and (c) — non-calculated flow modes [4]; (d) — 3D model of the nozzle studied in the calculation.

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3. Fig. 2. Section of the main computational grid (13 million cells) by the longitudinal plane of symmetry: (a) — full computational domain; (b) — zone near the nozzle.

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4. Fig. 3. Location of FWH control surfaces.

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5. Fig. 4. Location of observation points (microphones) in the far field: (a) — on an arc of a circle; (b) — in a set of azimuthal rings sweeping a cylindrical surface within the range –77 < x/D < 80.

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6. Fig. 5. Flow structure in the plane of symmetry of the jet: (a) — instantaneous field of the longitudinal velocity component, (b) — instantaneous pressure field (the arrow shows the orientation of the normal to the front of the dominant sound waves).

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7. Fig. 6. Distributions of the average value of the longitudinal velocity component: (a) — along the jet axis: 1 — calculation on a 6 million grid, 2 — calculation on a 13 million grid, 3 — measurement data [4], 4 — semi-empirical model [22]; (b) — radial profiles for different sections (1 – x/D = 4, 2 – x/D = 10): solid lines — calculation on a 13 million grid, dots and dashes — experiment [24].

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8. Fig. 7. (a) — Distribution of normalized mean value (I) and root-mean-quadratic value of pulsations (II) of the longitudinal velocity component along the jet axis; (b) — normalized spectra of pulsations of the longitudinal velocity component at a point on the jet axis x = 2Lc. 1 — measurement data for M = 0.53 [25]; 2 — calculation for M = 0.53 [12], 3 — calculation for M = 2, carried out in the present work; 4 — “–5/3” law.

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9. Fig. 8. Jet noise spectra at an angle of θ = 20° (red lines 1, 3, 5) and θ = 90° (blue lines 2, 4, 6): 1, 2 – experiment; 3, 4 – calculation on a grid of 6 million cells; 5, 6 – calculation on a grid of 13 million cells, the calculated noise spectra were obtained using the FWH2 control surface.

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10. Fig. 9. Comparison of calculated and measured jet noise directions for different Strouhal numbers: (a) — St = 0.12; (b) — 0.18; (c) — 0.3; (d) — 0.5. Markers — experiment, lines — calculation.

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11. Fig. 10. Directivity of azimuthal modes for (a) — St = 0.123 and (b) — St = 0.182. Markers — experiment [4], lines — calculation. 1 — mode, 2 — , 3 — , 4 — .

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12. Fig. 11. Spatial-frequency map of the total jet noise for a cylindrical surface R/D = 26.6 and its cross-section lines for analyzing the spectra and directivities of noise. A description of the figure is given in the text.

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13. Fig. 12. Spectra of the total noise (1) and individual azimuthal modes (2 — mode , 3 — sine and cosine modes , 4 — sine and cosine modes , 5 — mode ). (a) — x/D = –77; (b) — x/D = 7; (c) — x/D = 40. The vertical lines indicate the approximate boundary of frequencies correctly resolved in the calculation.

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14. Fig. 13. 1 — Spectrum of pressure pulsations on the jet axis at x/D = 1.2; 2, 3 — noise spectra in the far field at x/D = –77 for modes n = 0 and n = 1, respectively. For each case, spectra with a frequency resolution of ΔSt = 0.023 (solid lines) and ΔSt = 0.003 (dashed line) are shown. The vertical lines mark the boundaries of the resonant enhancement of the n = 0 (red) and n = 1 (blue) modes, calculated for a jet with M = 2 based on the tangential discontinuity model [37].

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15. Fig. 14. Normalized in accordance with (2) spectral densities of the noise power of jets in the lateral direction (θ = 90°): 1 — jet M = 2, experiment [4]; 2 — jet M = 2, calculation carried out in the present work (the vertical line indicates the approximate boundary of frequencies correctly resolved in the calculation); 3 — jet M = 0.53, experiment [40].

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16. Fig. 15. Directivity of azimuthal modes for different Strouhal numbers: (a) — St = 0.116; (b) — St = 0.186; (c) — St = 0.3. 1 — mode n = 0, 2 — n = 1, 3 — n = 2, 4 — n = 3.

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17. Fig. 16. Directivity of the axisymmetric mode at St = 0.3: (a) — on a linear scale; (b) — on a logarithmic scale. 1 — data from numerical modeling, 2 — calculation using the theory of instability waves [4].

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