Resonance Interaction of Wave Trains in Supersonic Boundary Layer

1996 ◽  
pp. 379-388 ◽  
Author(s):  
A. D. Kosinov ◽  
A. Tumin
Keyword(s):  
Boundary Layer ◽  
Supersonic Boundary Layer ◽  
Resonance Interaction ◽  
Wave Trains

Nonlinear interaction of wave trains in a supersonic boundary layer

1996 ◽  
Vol 8 (9) ◽  
pp. 2552-2554 ◽  
Author(s):  
Anatoli Tumin
Keyword(s):  
Boundary Layer ◽  
Nonlinear Interaction ◽  
Supersonic Boundary Layer ◽  
Wave Trains

Investigation of Influence of Spanwise Flow Nonuniformity on Controlled Disturbances Evolution in Supersonic Boundary Layer

2010 ◽  
Vol 5 (2) ◽  
pp. 17-27
Author(s):  
Aleksandra V. Panina ◽  
Aleksandr D. Kosinov ◽  
Yuri G. Yermolaev ◽  
Nikolay V. Semionov
Keyword(s):  
Boundary Layer ◽  
Wave Packet ◽  
Wave Train ◽  
Supersonic Boundary Layer ◽  
Fundamental Wave ◽  
Mean Flow ◽  
Flow Modulation ◽  
Wave Trains ◽  
Spanwise Flow ◽  
Flow Nonuniformity

Results of experimental study of influence of spanwise flow nonuniformity on the wave train evolution in supersonic boundary layer at Mach number M = 2 are presented. Spanwise modulation of mean flow in a boundary layer was created by means of labels from scotch tape by thickness of 60 and 110 microns. Downstream evolution of controlled disturbances was investigated. The wave characteristics of traveling disturbances were obtained. It was found that the wave trains development depends from size and location of the roughness. It is shown that the wave packet evolution qualitatively has the similar development in both cases as for the smooth surfaces. At the same time, the spanwise modulation of the mean flow leads to the fundamental wave excitation with high inclination angle. The phase spectra indicate that excitation of these waves takes place in the center of the wave packet. It was shown, that mean flow modulation can lead to stabilization of disturbance development in supersonic boundary layer on a flat plate.

A branch of self-oscillation in supersonic boundary layer

2020 ◽  
Author(s):  
N. M. Terekhova
Keyword(s):  
Boundary Layer ◽  
Supersonic Boundary Layer

Experimental study of natural disturbances of a supersonic boundary layer on a swept-wing model with periodic roughness

2020 ◽  
Author(s):  
A. A. Yatskikh ◽  
A. V. Panina ◽  
Yu. G. Yermolaev ◽  
A. D. Kosinov ◽  
N. V. Semionov
Keyword(s):  
Boundary Layer ◽  
Experimental Study ◽  
Supersonic Boundary Layer ◽  
Natural Disturbances ◽  
Swept Wing ◽  
Wing Model

Influence of coating permeability and roughness on supersonic boundary layer stability

2016 ◽  
Author(s):  
V. I. Lysenko ◽  
S. A. Gaponov ◽  
B. V. Smorodsky ◽  
Yu. G. Yermolaev ◽  
A. D. Kosinov ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Supersonic Boundary Layer ◽  
Boundary Layer Stability

Supersonic boundary layer on a plate. Comparison of calculation and experiment

1998 ◽  
Vol 33 (6) ◽  
pp. 864-875 ◽  
Author(s):  
V. G. Lushchik ◽  
A. E. Yakubenko
Keyword(s):  
Boundary Layer ◽  
Supersonic Boundary Layer

Experimental and Theoretical Investigation of the Supersonic Boundary Layer Stability on the Swept Wing

2008 ◽  
Vol 3 (3) ◽  
pp. 34-38
Author(s):  
Sergey A. Gaponov ◽  
Yuri G. Yermolaev ◽  
Aleksandr D. Kosinov ◽  
Nikolay V. Semionov ◽  
Boris V. Smorodsky
Keyword(s):  
Boundary Layer ◽  
Three Dimensional ◽  
Leading Edge ◽  
Supersonic Boundary Layer ◽  
Mean Flow ◽  
Swept Wing ◽  
Wing Model ◽  
Dimensional Boundary ◽  
The Stability ◽  
Good Agreement

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

scholarly journals On introduction of controlled disturbances into a longitudinal vortex in a supersonic boundary layer

2018 ◽  
Author(s):  
A. Panina ◽  
A. Kosinov ◽  
N. Semionov ◽  
Yu. Yermolaev
Keyword(s):  
Boundary Layer ◽  
Supersonic Boundary Layer ◽  
Longitudinal Vortex
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