Abstract
Steady air blowing (suction) into a turbulent boundary layer on the NACA 0012 airfoil through singular slots located on the opposite sides near the trailing edge is studied experimentally and numerically. The investigations are performed at the Reynolds number Rec = 0.7 · 106 in the range of the angles of attack α from −6 to 6°; the intensity of the injected and sucked jet characterized by a dimensionless momentum coefficient does not exceed 10−3. It is demonstrated that the result of blowing is not only an increase in the lift force, but also significant enhancement of the drag force of the airfoil. In the case of suction, the increase in the lift force is appreciably smaller despite airfoil drag reduction.
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