Experimental study of mean and pulsation flow characteristics in the 2D/3D supersonic boundary layer behind flat roughness elements

Panina, A. V.; Kosinov, A. D.; Yermolaev, Yu. G.; Gorev, V. N.; Семёнов, Н. В.

doi:10.1134/s0869864314010028

Cited by 16 publications

(3 citation statements)

References 11 publications

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“…The mean flow distortion was determined using the ratio between the relative change of the average mass flow and relative change of mean voltage output from the anemometer [23].…”

Section: Experimental Equipment and Data Processingmentioning

confidence: 99%

On the oblique breakdown mechanism in a supersonic boundary layer on a swept wing at Mach 2

Panina

Kosinov

Семёнов

et al. 2017

AIP Conference Proceedings

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Abstract.The results of an experimental study of the controlled pulsations development in the spanwise modulated boundary layer of a swept wing are presented in the paper. The experiments were conducted at Mach 2 and unit Reynolds number Re1 = 6×10 6 m -1 . The square stickers were applied to induce the spanwise modulation of mean flow in the boundary layer. It was obtained, that the presence of roughness leads to a decrease of the disturbance source efficiency at the subharmonic and fundamental frequency, and the oblique breakdown mechanism begins to appear at smaller values of the longitudinal coordinate x as compared with the case of a smooth wing.

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“…The mean flow distortion was determined using the ratio between the relative change of the average mass flow and relative change of mean voltage output from the anemometer [23].…”

Section: Experimental Equipment and Data Processingmentioning

confidence: 99%

On the oblique breakdown mechanism in a supersonic boundary layer on a swept wing at Mach 2

Panina

Kosinov

Семёнов

et al. 2017

AIP Conference Proceedings

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“…The experimental confirmation of the main concepts of the linear theory of stability in supersonic zero-pressure-gradient flow on a flat plate was obtained by this method in [1]. Also, this approach is useful in studies of laminar-turbulent transition in inhomogeneous and 3D supersonic boundary layers [2][3][4]. The approach of periodical disturbances is also used in direct numerical simulation studies (DNS).…”

Section: Introductionmentioning

confidence: 99%

Excitation of localized wave packet in swept-wing supersonic boundary layer

et al. 2017

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The evolution of the artificial wave packet in swept-wing supersonic boundary layer was experimentally studied at M=2. The localized disturbances were generated by a pulse glow discharge. Measurements were provided by a hot-wire anemometer. The spatial structure of the wave packet was studied. It was found that the wave packet has an asymmetric shape. In addition, the velocity of the propagation downstream of the wave packet was estimated.

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“…The disturbances with known initial characteristics are artificially introduced into the flow. The study of the evolution of artificial controlled perturbations allows one to find out the wave characteristics of the boundary layer [1][2][3][4][5][6]. Experiments with the controlled pulsations are very important and play a vital role in validating theoretical results.…”

Section: Introductionmentioning

confidence: 99%

The evolution of mass flow and total temperature pulsations in flat plate boundary layer at M=2.5

Yatskikh

Kolosov

Kosinov

et al. 2017

AIP Conference Proceedings

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Abstract. The work is devoted to the study of the regularities of laminar-turbulent transition in supersonic boundary layers. New experimental data are presented on the evolution downstream of natural disturbances in the boundary layer of a flat plate. The experiments were carried out in a low-noise supersonic wind tunnel T-325 of ITAM SB RAS at Mach number M=2.5. The measurements were made by a constant-temperature hot-wire anemometer in the scanning mode. The procedure of decomposition of the fluctuations of the boundary layer into temperature and mass flux disturbances is carried out.

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Experimental study of mean and pulsation flow characteristics in the 2D/3D supersonic boundary layer behind flat roughness elements

Cited by 16 publications

References 11 publications

On the oblique breakdown mechanism in a supersonic boundary layer on a swept wing at Mach 2

On the oblique breakdown mechanism in a supersonic boundary layer on a swept wing at Mach 2

Excitation of localized wave packet in swept-wing supersonic boundary layer

The evolution of mass flow and total temperature pulsations in flat plate boundary layer at M=2.5

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