Method laminar-turbulent transition control of supersonic boundary layer on a swept wing

Семёнов, Н. В.; Kosinov, A. D.

doi:10.1134/s0869864307030031

Cited by 23 publications

(12 citation statements)

References 6 publications

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“…Note work [14,17], which shows that the periodic surface roughness, located near the leading edge of the swept wing, can both stabilize boundary layer and accelerate the laminar-turbulent transition. The flow stabilization was caused by the impact of the distributed roughness to the stationary crossflow instability.…”

Section: Introductionmentioning

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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Section: Introductionmentioning

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 study of stability of a supersonic boundary layer on a swept wing [7] showed that the transition to turbulence here is caused by interaction of stationary (large-scale) and traveling (small-scale) disturbances. Hence, for controlling the laminar-turbulent transition in this case, it seems simpler and more effective to affect stationary structures whose character of evolution exerts a greater effect on the location of the transition region.…”

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confidence: 99%

“…The majority of investigations of the mechanism of turbulence emergence on an airfoil were performed at subsonic velocities [9][10][11]. Exceptions are the works described in [7,12,13], where stability of a supersonic boundary layer on a swept wing was studied. Ermolaev et al [12] considered natural traveling disturbances, and Semionov et al [7] and Kosinov et al [13] studied the evolution of artificial wave trains and their interaction with a stationary disturbance.…”

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confidence: 99%

Evolution of disturbances in a laminarized supersonic boundary layer on a swept wing

Семёнов

Ermolaev

Kosinov

2008

J Appl Mech Tech Phys

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Experimental data on stability of a three-dimensional supersonic boundary layer on a swept wing are presented. The experiments are performed on a swept wing model with a lenticular profile with a 40 • sweep angle of the leading edge at a zero angle of attack. The supersonic boundary layer on the swept wing was laminarized with the use of distributed roughness. A pioneering study of interaction of traveling and stationary disturbances is performed. Some specific features of this interaction are identified. The main reason for turbulence emergence in a supersonic boundary layer on a swept wing is demonstrated to be secondary crossflow instability.Introduction. The problem of turbulence emergence and development of methods of transition control in three-dimensional boundary layers has been studied by many researchers. Creating a small commercial supersonic aircraft of the new generation is supposed to involve new technologies, in particular, passive control of the laminarturbulent transition (flow laminarization) in the boundary layer with the use of microscale roughness distributed over the surface of a swept wing near the leading edge.It was shown [1, 2] that instability of the boundary layer on a swept wing can be controlled with the use of distributed roughness at subsonic flow velocities. The method of passive control has the following features. Microscale roughness elements are applied parallel to the leading edge of the wing, at a distance equal to 1-5% of the wing chord. Based on calculation results for the most unstable stationary mode, the spanwise step between the roughness elements is chosen, which should be approximately (0.50-0.55)λ st (λ st is the wavelength of the most unstable stationary mode in the direction parallel to the leading edge of the wing). The roughness elements used in [1, 2] were cylinders 6 μm high, which were located near the leading edge of the swept wing. A change in the spanwise distance between the roughness elements was found to affect the position of the laminar-turbulent transition region. For instance, the use of distributed roughness with a 12-mm step along the wing span (or with a step multiple to this value) made the transition region approach the leading edge approximately by 35%, while the use of an 8-mm step increased the laminar flow region by 11%.Distributed roughness was first used for passive control of the transition in a supersonic boundary layer on a swept wing in the experiments [3,4] with the use of the method developed for subsonic velocities [1,2]. Saric and Reed [3,4] reported that they used surface microroughness to delay the transition to turbulence in a three-dimensional boundary layer on a wing model with a subsonic leading edge. For a supersonic leading edge, the boundary layer was observed to remain laminar on the entire model. Even the use of roughness elements with a step λ st did not lead to boundary layer tripping. It should be noted that the values of the transition Reynolds numbers given in [3,4] are overrated by an order of magnitude. Zuccher et...

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“…Using roughness elements on the model allows us to obtain stationary waves with specified characteristics. The effect of distributed roughness on transition control in supersonic boundary layers on swept-wing models was studied in [14,15]. It was shown that the periodic surface roughness near the leading edge may stabilize the flow or move the laminar-turbulent transition closer to the leading edge of the model.…”

Section: Introductionmentioning

confidence: 99%

On the development of controlled stationary and travelling disturbances in the supersonic boundary layer of a swept wing

2017

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Abstract. Experimental data on the evolution of controlled stationary and travelling disturbances in a 3D supersonic boundary layer, over a 45° swept-wing at Mach number 2.0, is presented. Travelling artificial disturbances were introduced in the boundary layer by periodical glow discharge, at a frequency of 20 kHz. Stationary disturbances were acquired by setting the roughness elements on the surface of the model. Spatialtemporal and spectral-wave characteristics of the wave train at the frequency 20 kHz, in the linear region of development, were obtained. It was found that the periodic modulation of mean flow can lead to the stabilization of unstable travelling disturbances in the supersonic boundary layer of a swept wing. These experiments have investigated the viability of using roughness elements to control laminar-turbulent transition.

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Method laminar-turbulent transition control of supersonic boundary layer on a swept wing

Cited by 23 publications

References 6 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

Evolution of disturbances in a laminarized supersonic boundary layer on a swept wing

On the development of controlled stationary and travelling disturbances in the supersonic boundary layer of a swept wing

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