Results of the controlled disturbance experiments in the supersonic boundary layer on a swept wing are considered. The high-frequency glow discharge technique is used for the disturbance generation. The linear development of wave trains is tested in smooth and rough surface conditions of the models. The relative receptivity of a three-dimensional (3D) boundary layer to stationary and nonstationary disturbances is estimated. Obtained that by using microroughness elements located in a swept wing boundary layer, it is possible to get a damping e¨ect on the linear development of a spatial wave packet in the near ¦eld of the disturbances source.
Abstract.The results of an experimental study of the controlled pulsations development in the spanwise modulated boundary layer of a swept wing are presented in the paper. The experiments were conducted at Mach 2 and unit Reynolds number Re1 = 6×10 6 m -1 . The square stickers were applied to induce the spanwise modulation of mean flow in the boundary layer. It was obtained, that the presence of roughness leads to a decrease of the disturbance source efficiency at the subharmonic and fundamental frequency, and the oblique breakdown mechanism begins to appear at smaller values of the longitudinal coordinate x as compared with the case of a smooth wing.
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