Abstract

An experimental study of the influence of the boundary layer suction distributed over the surface on the stationary disturbance generated upstream was carried out on a straight wing model at subsonic flow velocities. A localized three-dimensional roughness element was used to excite stationary disturbances near the leading edge. Using the hot-wire method, quantitative data were obtained on the structure of the flow behind the roughness downstream with and without suction. It was shown that using the technique of suction of the boundary layer, inside which a stationary disturbance propagates, it is possible to reduce the level of pulsations by 4.6 times.

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