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...

Full description

Saved in:
Bibliographic Details
Published inJournal of engineering physics and thermophysics Vol. 98; no. 1; pp. 215 - 218
Main Authors Egorov, I. V., Palchekovskaya, N. V.
Format Journal Article
LanguageEnglish
Published New York Springer US 01.01.2025
Springer Nature B.V
Subjects
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
direct numerical simulation
nonlinear stage
laminar-turbulent transition
supersonic flow
Online AccessGet full text
ISSN1062-0125
1573-871X
DOI10.1007/s10891-025-03092-4

Cover

More Information
Summary: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°.
Bibliography:ObjectType-Article-1
SourceType-Scholarly Journals-1
ObjectType-Feature-2
content type line 14
ISSN:1062-0125
1573-871X
DOI:10.1007/s10891-025-03092-4