On the artificial disturbance evolution in 2D/3D spanwise modulated supersonic boundary layers

On the oblique breakdown mechanism in a supersonic boundary layer on a swept wing at Mach 2

“…For application of the active or passive methods for control of transition or friction on the surface, it is necessary to consider that actuators can be installed in non-ideal conditions, and their effectiveness may be different, including the changing of the characteristics of the flight. In the papers [15,16] it was shown that the presence of roughness in front of the source of artificial disturbances can lead to both an increase and a decrease in its effective power. Therefore, the study of features of disturbance generation by controlled actuators to create a technology control of the transition or the surface friction of the aircraft is relevant.…”

“…In [15] it was found that the presence of roughness leads to the stabilization of the wave packet development at the subharmonic and fundamental frequency at Mach 2.5 in the boundary layer on the swept wing. At Mach 2, the transverse modulation of the mean flow had a major influence on the effective power of the perturbation source, while the spectral composition of the perturbations and the growth rate remained the same on the smooth wing and on the wing with roughness.…”

“…Herewith the oblique breakdown mechanism was weakly expressed. In the present experiments, the electric power of the source was increased in comparison with [15], in order to increase the introduced perturbations amplitude, which leads to an intensification of the nonlinear mechanisms of disturbance interaction. This paper presents results on the generation and development of artificial disturbances and receptivity to controlled pulsations in spanwise modulated supersonic boundary layer on a swept wing at Mach 2.…”