Evolution of wave packets in supersonic flat-plate boundary layer

Yatskikh, A. A.; Ermolaev, Yu. G.; Kosinov, A. D.; Семёнов, Н. В.

doi:10.1134/s0869864314010023

Cited by 33 publications

(16 citation statements)

References 7 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Artificial localized disturbances can be excited in the boundary layer by means of impulse action. In the case of supersonic flows, localized disturbances can be excited by a pulsed electric discharge [1,2]. It was shown in [2] that the energy and duration of the pulsed discharge affect on the localized perturbations generated in the supersonic boundary layer.…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical investigation of excitation of artificial disturbances in the supersonic boundary layer

et al. 2019

View full text Add to dashboard Cite

The influence of the parameters of the impulse action on the laminar supersonic flat-plate boundary layer on the excited localized perturbations is investigated at Mach 2. The influence of the duration of a pulsed discharge on the generated disturbances is studied experimentally. Also, a direct numerical simulation of the influence of the parameters of pulse injection on generated perturbations is carried out. It is obtained that as the duration of the action on the supersonic boundary layer increases, the amplitude of the generated disturbance increases. The velocity of the propagation downstream of localized disturbances in Mach 2 supersonic flat-plate boundary layer is estimated.

show abstract

Section: Introductionmentioning

confidence: 99%

Experimental and numerical investigation of excitation of artificial disturbances in the supersonic boundary layer

et al. 2019

View full text Add to dashboard Cite

show abstract

“…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

View full text Add to dashboard Cite

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.

show abstract

“…In papers [1][2][3][4] for supersonic and subsonic oncoming flow velocities, such investigations were carried out on the excitation of longitudinal structures and controlled wave packets in the boundary layer. This method makes it possible detailed investigations of characteristics for artificially introduced perturbations with saving of phase information, to trace the dynamics of the development of a concrete perturbation at all its stages.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation of localized disturbances in the straight wing boundary layer, generated by finite surface vibrations

Козлов

Катасонов

Pavlenko

2017

AIP Conference Proceedings

View full text Add to dashboard Cite

Abstract. Downstream development of artificial disturbances were investigated experimentally using hot-wire constant temperature anemometry. It is shown that vibrations with high-amplitude of a three-dimensional surface lead to formation of two types of perturbations in the straight wing boundary layer: streamwise oriented localized structures and wave packets. The amplitude of streamwise structure is decay downstream. The wave packets amplitude grows in adverse pressure gradient area. The flow separation is exponentially intensified of the wave packet amplitude.

show abstract

Evolution of wave packets in supersonic flat-plate boundary layer

Cited by 33 publications

References 7 publications

Experimental and numerical investigation of excitation of artificial disturbances in the supersonic boundary layer

Experimental and numerical investigation of excitation of artificial disturbances in the supersonic boundary layer

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

Experimental investigation of localized disturbances in the straight wing boundary layer, generated by finite surface vibrations

Contact Info

Product

Resources

About