Abstract
An experimental work of continuous normal suction from the wing upper surface effects on the aerodynamic forces is carried out, as well as, the effect of normal suction slot channels location and the mass flow rate sucked strength are involved in this study. The wing model with NACA-0015 has been made to achieve normal suction from the wing upper surface by means of four slot channels. The satisfaction of the suction is done by using vacuum pump. The tests are to be done for incompressible flow over wing with and without a continuous normal suction for three different angle of attack 8, 12 and 16 Deg., and for three different Reynolds numbers 13.6×104, 20.4×104 and 24.5×104. The results showed that the continuous normal suction can significantly increase the lift to drag force ratio, and this ratio is increasing more as the strength of the suction increases. Keywords : Aerodynamic – Incompressible Flow – Boundary Layer Control – Normal Suction– Experimental work – Lift and Drag Coefficient
Highlights
The flow separation is mostly an undesirable phenomenon, because it entails large energy losses and in most applications adversely affects the aerodynamic loads in the form of lift loss and drag increase
It can be found that the continuous normal suction from the upper surface of the wing has positive effect on the lift coefficient, since the lift coefficient increased due to suction, and as the magnitude of suction increases, the increasing in the lift coefficient is increasing more
The suction has a negative effect on the drag coefficient, its values increase as the magnitudes of suction increase
Summary
The flow separation is mostly an undesirable phenomenon, because it entails large energy losses and in most applications adversely affects the aerodynamic loads in the form of lift loss and drag increase. Wall suction and blowing have been encountered in many aeronautical engineering problems such as delaying or preventing the separation from the upper airfoil surface, and enhance airfoil wake flow structure. 2005, [4], studied the suction near the leading edge as a means of controlling separation and thereby inhibiting dynamic stall, high-speed incompressible flow past a thin airfoil in a uniform stream was considered, by using steady and unsteady boundary-layer solutions. 2008, [6], presented a numerical simulation study of unsteady incompressible laminar flow over a NACA 0015 airfoil with and without a continuous wallnormal suction and blowing as an active boundary layer control technique. The use of continuous wall-normal suction and blowing from upper and lower surface of the airfoil, respectively, is an effective idea to prevent or delay the flow separation and enhance airfoil wake flow structure. The present work is an experimental, applying a continuous normal suction rate from upper wing surface to enhance the lift, drag force and their ratio
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