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 fi rst 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 coeffi cients and critical amplitudes of the longitudinal component of pulsations of the fl ow-velocity vector in a supersonic boundary layer on a fl at plate at angles of attack of 0 and 5^o .
Consideration is given to the excitation and development of the fi rst 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 coeffi cients and critical amplitudes of the longitudinal component of pulsations of the fl ow-velocity vector in a supersonic boundary layer on a fl at plate at angles of attack of 0 and 5^o .
Author:  I. V. Egorov, N. V. Palchekovskaya
Keywords:  laminar-turbulent transition, nonlinear stage, supersonic fl ow, direct numerical simulation
Page:  215