Numerical Simulation of the Nonlinear Stage of Laminar-Turbulent Transition in a Supersonic Boundary Layer in the Presence of Acoustic Disturbances
Consideration is given to the excitation and development of the first mode of instability on a plate at the free-stream Mach number M = 3, a nearly adiabatic wall temperature, and the Reynolds number Re ∞ = 2·10 7 . Based on direct numerical simulation, the authors have obtained the values of recept...
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| Published in | Journal of engineering physics and thermophysics Vol. 98; no. 1; pp. 215 - 218 |
|---|---|
| Main Authors | , |
| Format | Journal Article |
| Language | English |
| Published |
New York
Springer US
01.01.2025
Springer Nature B.V |
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| Online Access | Get full text |
| ISSN | 1062-0125 1573-871X |
| DOI | 10.1007/s10891-025-03092-4 |
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| Abstract | Consideration is given to the excitation and development of the first mode of instability on a plate at the free-stream Mach number M = 3, a nearly adiabatic wall temperature, and the Reynolds number Re
∞
= 2·10
7
. Based on direct numerical simulation, the authors have obtained the values of receptivity coefficients and critical amplitudes of the longitudinal component of pulsations of the flow-velocity vector in a supersonic boundary layer on a flat plate at angles of attack of 0 and 5°. |
|---|---|
| AbstractList | Consideration is given to the excitation and development of the first mode of instability on a plate at the free-stream Mach number M = 3, a nearly adiabatic wall temperature, and the Reynolds number Re
∞
= 2·10
7
. Based on direct numerical simulation, the authors have obtained the values of receptivity coefficients and critical amplitudes of the longitudinal component of pulsations of the flow-velocity vector in a supersonic boundary layer on a flat plate at angles of attack of 0 and 5°. Consideration is given to the excitation and development of the first mode of instability on a plate at the free-stream Mach number M = 3, a nearly adiabatic wall temperature, and the Reynolds number Re∞ = 2·107. Based on direct numerical simulation, the authors have obtained the values of receptivity coefficients and critical amplitudes of the longitudinal component of pulsations of the flow-velocity vector in a supersonic boundary layer on a flat plate at angles of attack of 0 and 5°. |
| Author | Egorov, I. V. Palchekovskaya, N. V. |
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| Keywords | direct numerical simulation nonlinear stage laminar-turbulent transition supersonic flow |
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| References | 3092_CR1 IV Egorov (3092_CR5) 2008; 601 Receptivity to free-stream sound (3092_CR2) 2003; 488 AV Fedorov (3092_CR6) 1991; 9 3092_CR4 IV Egorov (3092_CR10) 2016; 56 Effects of different types of free-stream disturbances (3092_CR3) 2005; 532 AV Fedorov (3092_CR7) 1993; 151 AA Maslov (3092_CR9) 2001; 426 AV Fedorov (3092_CR8) 2003; 491 |
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| SubjectTerms | Angle of attack Boundary layer transition Classical Mechanics Complex Systems Direct numerical simulation Engineering Engineering Thermodynamics Flat plates Flow velocity Heat and Mass Transfer Hydrogasdynamics in Technological Processes Industrial Chemistry/Chemical Engineering Mach number Reynolds number Simulation Supersonic boundary layers Thermodynamics Wall temperature |
| Title | Numerical Simulation of the Nonlinear Stage of Laminar-Turbulent Transition in a Supersonic Boundary Layer in the Presence of Acoustic Disturbances |
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