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Experiments on the Artificial Disturbance Evolution in 2D and 3D Spanwise Modulated Boundary Layers at Mach 2 and 2.5. / Kosinov, Alexander; Panina, Alexandra; Kolosov, Gleb et al.

In: Procedia IUTAM, Vol. 14, 2015, p. 48-57.

Research output: Contribution to journal › Conference article › peer-review

Harvard

Kosinov, A, Panina, A, Kolosov, G, Semionov, N & Yermolaev, Y 2015, 'Experiments on the Artificial Disturbance Evolution in 2D and 3D Spanwise Modulated Boundary Layers at Mach 2 and 2.5', Procedia IUTAM, vol. 14, pp. 48-57. https://doi.org/10.1016/j.piutam.2015.03.023

APA

Kosinov, A., Panina, A., Kolosov, G., Semionov, N., & Yermolaev, Y. (2015). Experiments on the Artificial Disturbance Evolution in 2D and 3D Spanwise Modulated Boundary Layers at Mach 2 and 2.5. Procedia IUTAM, 14, 48-57. https://doi.org/10.1016/j.piutam.2015.03.023

Vancouver

Kosinov A, Panina A, Kolosov G, Semionov N, Yermolaev Y. Experiments on the Artificial Disturbance Evolution in 2D and 3D Spanwise Modulated Boundary Layers at Mach 2 and 2.5. Procedia IUTAM. 2015;14:48-57. doi: 10.1016/j.piutam.2015.03.023

Author

Kosinov, Alexander ; Panina, Alexandra ; Kolosov, Gleb et al. / Experiments on the Artificial Disturbance Evolution in 2D and 3D Spanwise Modulated Boundary Layers at Mach 2 and 2.5. In: Procedia IUTAM. 2015 ; Vol. 14. pp. 48-57.

BibTeX

@article{32595b5856394713a3d6e04cdb312c59,
title = "Experiments on the Artificial Disturbance Evolution in 2D and 3D Spanwise Modulated Boundary Layers at Mach 2 and 2.5",
abstract = "Experimental data on the nonlinear wave train development in 3D supersonic boundary layer over swept wing and experimental investigation of wave train development in spanwise modulated boundary layer on flat plate and swept wing at Mach number 2 and 2.5 are presented. Artificial disturbances in the boundary layer were excited by periodical glow discharge mainly at 10 and 20 kHz. It was found, that some disturbance excitation downstream cannot be explained by linear stability theory. It was obtained that receptivity of supersonic boundary layer to the surface excited controlled pulsations and the wave train development essentially depends on the Mach number.",
keywords = "artificial disturbance, boundary layer, experiments, flat palate, laminar-turbulent transition, microroughness, nonlinearity, supersonic flow, swept wing",
author = "Alexander Kosinov and Alexandra Panina and Gleb Kolosov and Nikolay Semionov and Yury Yermolaev",
year = "2015",
doi = "10.1016/j.piutam.2015.03.023",
language = "English",
volume = "14",
pages = "48--57",
journal = "Procedia IUTAM",
issn = "2210-9838",
note = "8th IUTAM-ABCM Symposium on Laminar Turbulent Transition, LTT 2014 ; Conference date: 08-09-2014 Through 12-09-2014",

}

RIS

TY - JOUR

T1 - Experiments on the Artificial Disturbance Evolution in 2D and 3D Spanwise Modulated Boundary Layers at Mach 2 and 2.5

AU - Kosinov, Alexander

AU - Panina, Alexandra

AU - Kolosov, Gleb

AU - Semionov, Nikolay

AU - Yermolaev, Yury

PY - 2015

Y1 - 2015

N2 - Experimental data on the nonlinear wave train development in 3D supersonic boundary layer over swept wing and experimental investigation of wave train development in spanwise modulated boundary layer on flat plate and swept wing at Mach number 2 and 2.5 are presented. Artificial disturbances in the boundary layer were excited by periodical glow discharge mainly at 10 and 20 kHz. It was found, that some disturbance excitation downstream cannot be explained by linear stability theory. It was obtained that receptivity of supersonic boundary layer to the surface excited controlled pulsations and the wave train development essentially depends on the Mach number.

AB - Experimental data on the nonlinear wave train development in 3D supersonic boundary layer over swept wing and experimental investigation of wave train development in spanwise modulated boundary layer on flat plate and swept wing at Mach number 2 and 2.5 are presented. Artificial disturbances in the boundary layer were excited by periodical glow discharge mainly at 10 and 20 kHz. It was found, that some disturbance excitation downstream cannot be explained by linear stability theory. It was obtained that receptivity of supersonic boundary layer to the surface excited controlled pulsations and the wave train development essentially depends on the Mach number.

KW - artificial disturbance

KW - boundary layer

KW - experiments

KW - flat palate

KW - laminar-turbulent transition

KW - microroughness

KW - nonlinearity

KW - supersonic flow

KW - swept wing

UR - http://www.scopus.com/inward/record.url?scp=84940668398&partnerID=8YFLogxK

U2 - 10.1016/j.piutam.2015.03.023

DO - 10.1016/j.piutam.2015.03.023

M3 - Conference article

AN - SCOPUS:84940668398

VL - 14

SP - 48

EP - 57

JO - Procedia IUTAM

JF - Procedia IUTAM

SN - 2210-9838

T2 - 8th IUTAM-ABCM Symposium on Laminar Turbulent Transition, LTT 2014

Y2 - 8 September 2014 through 12 September 2014

ER -

ID: 25840700