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Experimental investigation in turbulent boundary layer flows represents one of the canonicalgeometries of wall bounded shear flows. Utmost relevance of such experiments, however,is applied in the engineering applications in aerospace and marine industries. Inparticular, continuous effort is being imparted to explore the underlying physics of theflow in order to develop models for numerical tools and to achieve flow control. Flowcontrol experiments have been widely investigated since 1930¿s. Several flow controltechnique has been explored and have shown potential benefit. But the choice of controltechnique depends largely on the boundary condition and the type of application.Hence, friction drag of subsonic transport aircraft is intended to be reduced within thescope of this Ph. D. topic. Therefore, application of active control method such as microblowingeffect in the incompressible, zero pressure gradient turbulent boundary layer wasinvestigated. A series of experiments have been performed in two different wind tunnelfacilities. Wind tunnel from Department of Aerodynamics and Fluid Mechanics (LAS)was used for the measurements for moderate Reynolds number range in co-operationwith the wind tunnel from Laboratoire de M¿ecanique de Feiret Lille for large Reynoldsnumber range. Measurements are conducted with the help of state-of-the-art techniquessuch as Laser Doppler Anemometry, Particle Image Velocimetry and electronic pressuresensors.

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