Abstract
—The linear and nonlinear stages of disturbance development in the supersonic boundary layer over a 10° expansion corner is investigated numerically within the framework of Navier—Stokes equations for Mach number 3. The effect of sudden flow expansion on the disturbance evolution is analyzed. The flow stabilization effect observable in the aerodynamic experiment is also discussed.
Highlights
IntroductionIt was noted that small-scale structures are considerably suppressed immediately behind a rarefaction fan
An investigation of subsonic turbulent flows in the presence of a large negative pressure gradient showed the possibility of complete boundary layer relaminarization [2,3,4,5], which is connected with the curved nature of streamlines and favorable longitudinal and normal pressure gradients which lead to a rapid diminishing of the turbulent fluctuation scale in the flow acceleration region [6]
Within the framework of Navier—Stokes equations the development of wave packets and turbulent spots in a supersonic boundary layer (Mach number 3) over a 10° expansion corner is investigated numerically
Summary
It was noted that small-scale structures are considerably suppressed immediately behind a rarefaction fan These inferences were confirmed in experiments at Mach number 4.9 [9, 10], where it was found that the intermittence region of the boundary layer shortens in an acceleration flow being displaced toward the boundary layer edge. It was noted that the relaminarization criteria obtained at subsonic velocities can be applied at large supersonic velocities
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