Titlebook: New Results in Numerical and Experimental Fluid Mechanics II; Contributions to the Wolfgang Nitsche,Hans-Joachim Heinemann,Reinhard H Book

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Control of flow separation by dynamic excitation of the free shear layer,d blowing through a narrow slot close to the leading edge of the airfoil. A small cavity below the slot was connected to a horn-driver providing periodic pressure fluctuations to drive the flow through the slot. The present research confirms the results of previous studies [1] that the mechanism for

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On Active Control of Boundary Layer Instabilities on a Wing,in a reduction of the viscous friction drag. One less known approach is the reduction of natural occurring instability waves, so called Tollmien-Schlichting-waves (TS-waves) of a laminar boundary layer by means of superposition with artificially excited canceling waves. For technical applications of

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