scholarly journals The effect of small angle of attack on the laminar-turbulent transition in boundary layer on swept wing at Mach number M=2

2017 ◽  
Author(s):  
N. V. Semionov ◽  
Yu. G. Yermolaev ◽  
A. D. Kosinov ◽  
A. N. Semenov ◽  
B. V. Smorodsky ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Mach Number ◽  
Small Angle ◽  
Angle Of Attack ◽  
Swept Wing ◽  
Turbulent Transition ◽  
Laminar Turbulent Transition

scholarly journals An effect of small angle of attack on disturbances evolution in swept wing boundary layer at Mach number M=2

2018 ◽  
Author(s):  
N. V. Semionov ◽  
Yu. G. Yermolaev ◽  
V. L. Kocharin ◽  
A. D. Kosinov ◽  
A. N. Semenov ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Mach Number ◽  
Small Angle ◽  
Angle Of Attack ◽  
Swept Wing

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

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.

scholarly journals Large-eddy simulation of laminar-turbulent transition in a swept-wing boundary layer

1997 ◽  
Author(s):  
Xiaoli Huai ◽  
Ugo Piomelli ◽  
Ronald Joslin ◽  
Xiaoli Huai ◽  
Ugo Piomelli ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Large Eddy Simulation ◽  
Swept Wing ◽  
Eddy Simulation ◽  
Turbulent Transition ◽  
Large Eddy ◽  
Laminar Turbulent Transition

scholarly journals Influence of Small Angles of Attacks on the Laminar- Turbulent Transition on a Swept Wing at Mach Number M = 2

2017 ◽  
Vol 12 (3) ◽  
pp. 35-40 ◽  
Author(s):  
Yu. G. Yermolaev ◽  
◽  
A. D. Kosinov ◽  
V. S. Kosorygin ◽  
N. V. Semionov ◽  
...  
Keyword(s):  
Mach Number ◽  
Swept Wing ◽  
Turbulent Transition ◽  
Laminar Turbulent Transition

scholarly journals Experimental Study of the Influence of Unit Reynolds Number on the Laminar-Turbulent Transition on the Model Swept Wing with a Subsonic Leading Edge at M = 2

2021 ◽  
Vol 16 (1) ◽  
pp. 44-52
Author(s):  
Vasilii L. Kocharin ◽  
Nikolai V. Semionov ◽  
Alexander D. Kosinov ◽  
Aleksey A. Yatskikh ◽  
Sofia A. Shipul ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Experimental Studies ◽  
Leading Edge ◽  
Supersonic Boundary Layer ◽  
Swept Wing ◽  
Unit Reynolds Number ◽  
Flow Parameters ◽  
Turbulent Transition ◽  
Laminar Turbulent Transition

Experimental studies of the influence of unit Reynolds number on the laminar-turbulent transition in a supersonic boundary layer of a swept wing with a subsonic leading edge at Mach number 2 are performed. The experiments were performed on a model of a swept wing with a swept angle of the leading edge of 72 degrees and with a 3% profile with a variable chord length in span. The hot-wire measurements showed that a laminar-turbulent transition in a supersonic boundary layer of a swept wing with a subsonic leading edge occurs earlier (~25-30%) than on a model with a supersonic leading edge with the same oncoming flow parameters. It is shown that a change unit Reynolds number insignificant influence the laminar-turbulent transition in the boundary layer of a swept wing with a subsonic leading edge.

scholarly journals Validation of a laminar-turbulent transition prediction technique for a swept-wing boundary-layer flow

2021 ◽  
Vol 2057 (1) ◽  
pp. 012081
Author(s):  
A V Boiko ◽  
V I Borodulin ◽  
A V Ivanov ◽  
S V Kirilovskiy ◽  
D A Mischenko ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Wind Tunnel ◽  
Test Section ◽  
Wind Tunnel Test ◽  
Cross Flow ◽  
Infrared Camera ◽  
Main Flow ◽  
Swept Wing ◽  
Turbulent Transition ◽  
Laminar Turbulent Transition

Abstract The laminar-turbulent transition in the boundary layer of a 45° swept wing model installed at zero attack angle in the test section of a subsonic wind-tunnel was detected with the help of an infrared camera. The camera recorded sequences of frames, the evolution of the preheated model surface temperature acquired and used for differentiating between the laminar and turbulent regions. The transition onset was evaluated at both sides of the model. Corresponding main flow computations in the virtual wind tunnel test section were performed at the same flow conditions with ANSYS Fluent. The computed main-flow velocity profiles along inviscid streamlines were used for analysis of hydrodynamic stability of the boundary layer with respect to Tollmien-Schlichting waves and stationary cross-flow vortices to obtain N-factor distributions along the model chord. A comparison of the experimental and the computed transition onsets was performed.

Simulation of the laminar-turbulent transition in the boundary layer of the swept wing in the subsonic flow at angles of attack

2020 ◽  
Author(s):  
S. V. Kirilovskiy ◽  
A. V. Boiko ◽  
K. V. Demyanko ◽  
Y. M. Nechepurenko ◽  
T. V. Poplavskaya
Keyword(s):  
Boundary Layer ◽  
Subsonic Flow ◽  
Swept Wing ◽  
Turbulent Transition ◽  
Laminar Turbulent Transition
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