Experimental investigation of development of disturbances in a supersonic boundary layer on a swept wing
N.V. Semionov, Yu.G. Yermolaev, A.D. Kosinov, and V.Ya. Levchenko
Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia
Pages: 347–357
Abstract
The experimental data of stability of a 3D supersonic boundary layer on a swept wing are presented. Development of artificial wave trains and their interaction with a steady disturbance have been studied. The experiments have been performed on a swept wing with a lenticular airfoil at swept angle of the leading edge 40o and under zero angle of attack. The wave characteristics of travelling disturbances were determined. It was found that evolution of the controlled disturbances at an energy-carrier frequencies is similar to the development of the travelling waves for subsonic velocities. It results from the investigations that a nature of the stability in gradient-plane and spatial supersonic boundary layers is radically different. It is shown that a crossflow secondary instability is the main mechanism of a turbulence initiation in the supersonic boundary layer on the swept wing.
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