Experiments on relative receptivity of three-dimensional supersonic boundary layer to controlled disturbances and its development

Abstract

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.

On the relative “receptivity” of twoand three-dimensional supersonic boundary layers to stationary disturbances at mach 2

“…It has been also shown that the location of labels relative to the disturbance source aperture has di¨erent in §uence to the mean §ow characteristics and to the initial controlled disturbance amplitude. An additional mean §ow distortion was found [29], if the aperture was in the sticker wake. This e¨ect certainly requires further investigation, as it may limit the development of future transition §ow control technologies at supersonic speeds.…”

“…The aperture coordinates on the plate are x = 37 ± 0.25 mm and z = 0 (here, x is the distance from the leading edge and z = 0 corresponds to the centerline of the model symmetry). Swept wing model was plane-convex pro¦le and contained a disturbance source aperture of 0.41 mm in diameter [29]. The aperture coordinates on the working surface of the swept wing are x = 57.7 ± 0.25 mm and z = 0.…”

The evolution of mass flow and total temperature pulsations in flat plate boundary layer at M=2.5

“…It is possible to obtain data on the amplitude of total temperature and mass flux pulsations by measurements at different values of the probe overheating. In application of laminar-turbulent transition studies the most progress was achieved in works [15,16]. The decomposition of the pulsations of the supersonic boundary layer on the mass flow and total temperature fluctuation was provided with the help of a constant-temperature hot-wire anemometer with the possibility of automatic scanning by probe overheating.…”