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 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

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

Sensitivity of a supersonic boundary layer to acoustic disturbances

1992 ◽  
Vol 27 (1) ◽  
pp. 29-34 ◽  
Author(s):  
A. V. Fedorov ◽  
A. P. Khokhlov
Keyword(s):  
Boundary Layer ◽  
Supersonic Boundary Layer ◽  
Acoustic Disturbances
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