Publisher:Khulna University of Engineering & Technology (KUET), Khulna, Bangladesh.
Abstract:
In this research a new concept of flow separation control mechanism has been
introduced to improve the aerodynamic characteristics of an airfoil. Control of flow
separation over an airfoil which experiences a laminar separation bubble for a low
Reynolds number is experimentally simulated under the effects of suction and injection.
The suction and injection control mechanism appears to be suppression of the
separation bubble and reduction of the upper surface pressure to increase the lift and
decrease the drag. To perform the experiment of NACA 2415 airfoil profile has been
chosen to make wing model. The wing model with control mechanism has been tested
in a sub-sonic wind tunnel. The experiments are performed with different angle of
aUack and different suction-injection frequency. The experimental results show that the
flow separation control is possible by the proposed mechanism and benefits can be
achieved by suction and injection. The wing performance is significantly improved due
to control of flow separation by suction and injection. It has also been found that the lift
increases about 14% and drag reduces about 23% at the angle of attack 8 degree.
This thesis is submitted to the Department of Mechanical Engineering, Khulna University of Engineering & Technology in partial fulfillment of the requirements for the degree of Master of Science in Mechanical Engineering, May 2010.
Cataloged from PDF Version of Thesis.
Includes bibliographical references (pages 57-59).
