Experimental investigation of the natural and controlled disturbance development in a supersonic boundary layer on the swept wing

Theoretical and an experimental research results of the disturbances development in a swept wing boundary layer are presented at Mach number М = 2. In experiments development of natural and small amplitude controllable disturbances downstream was studied. Experiments were carried out on a swept wing model with a lenticular profile at a zero attack angle. The swept angle of a leading edge was 40°. Wave parameters of moving disturbances were determined. In frames of the linear theory and an approach of the local self-similar mean flow the stability of a compressible three-dimensional boundary layer is studied. Good agreement of the theory with experimental results for transversal scales of unstable vertices of the secondary flow was obtained. However the calculated amplification rates differ from measured values considerably. This disagreement is explained by the nonlinear processes observed in experiment

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Excitation Of Localized Wave Packet In 3d Supersonic Boundary Layer

Siberian Journal of Physics ◽

10.54362/1818-7919-2017-12-1-57-65 ◽

2017 ◽

Vol 12 (1) ◽

pp. 57-65

Author(s):

Alex Yatskih ◽

Marina Rumenskikh ◽

Yuri Yermolaev ◽

Aleksandr Kosinov ◽

Nikolay Semionov ◽

...

Keyword(s):

Boundary Layer ◽

Wave Packet ◽

Wave Packets ◽

Leading Edge ◽

Supersonic Boundary Layer ◽

Swept Wing ◽

Sweep Angle ◽

Asymmetric Shape ◽

Pulse Electric ◽

Pulse Electric Discharge

The results of experimental study of excitation of localized in time and space controlled disturbances (wave packets) in a supersonic swept-wing boundary layer are presented. The experiments were performed at Mach number M = 2 on the model of wing with a lenticular profile and a 40 degrees sweep angle of the leading edge at zero angle of attack. Wave packets were generated by a pulse electric discharge on the surface of the model. A structure of controlled wave packet was studied. It was found that the wave packet has an asymmetric shape. Comparison with the case of twodimensional boundary layer was done.

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The influence of moderate angle-of-attack variation on disturbances evolution and transition to turbulence in supersonic boundary layer on swept wing

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410019852804 ◽

2019 ◽

Vol 234 (1) ◽

pp. 96-101

Author(s):

Alexander Kosinov ◽

Nikolai Semionov ◽

Yury Yermolaev ◽

Boris Smorodsky ◽

Gleb Kolosov ◽

...

Keyword(s):

Boundary Layer ◽

Theoretical Study ◽

Angle Of Attack ◽

Reynolds Numbers ◽

Supersonic Boundary Layer ◽

Linear Stability Theory ◽

Transition To Turbulence ◽

Computational Results ◽

Swept Wing ◽

Turbulent Transition

The paper is devoted to an experimental and theoretical study of effect of moderate angle-of-attack variation on disturbances evolution and laminar-turbulent transition in a supersonic boundary layer on swept wing at Mach 2. Monotonous growth of the transition Reynolds numbers with angle of attack increasing from −2° to 2.7° is confirmed. For the same conditions, calculations based on linear stability theory are performed. The experimental and computational results show a favourable comparison.

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