Experimental Investigation of Separation and Stability of Supersonic Laminar Boundary Layer

Experimental investigation has been carried out of the development of perturbations in separation zone of supersonic boundary layer with laminar flow-around of the model of the cones with varying angle of taper: α/2=5° and 10°. The Mach number of the incident flow equals 2.0. Frequency-wave characteristics of disturbances and mean flow parameters in separation zone have been determined.