Abstract
The efficiency of steady air blowing / suction into the turbulent boundary layer of the NACA 0012 aerofoil section in an incompressible flow was studied experimentally. The blowing / suction was carried out through finely perforated sections located on the adjacent sides of the wing and being parts of its streamlined surface. The studies were performed at the Reynolds number Re c = 0.7x10 6 in the range of angles of attack a = -6 - 6o. The obtained results clearly indicate the ambiguous nature of the combined control action in the form of blowing / suction on the aerofoil aerodynamic characteristics. The maximum gain in lift-to-drag ratio of about 1.8 units is achieved at zero angle of attack a . An increase in a leads to a decrease in the effectiveness of this method of action on the boundary layer.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
