Experimental Assessment of the Aerodynamics of a Slotted Wavy Blade

Many techniques have been incorporated into the design of turbine blades in an attempt to improve their performance. Assessment is applied to investigate the flow behaviour around NACA 0012 with modifications (slotted and wave slotted airfoil) experimentally. An open subsonic wind tunnel with a test section of (30.5 ×30.5×60 cm) was employed to conduct the test. The work experiment investigated two modified models (slotted and hybrid slotted and wavy) then compared them to the normal blade model. A slotted blade NACA 0012 airfoil model with a slot width of 1.5 mm at 60% of the chord was employed in the current study. All blades exhibited stall between 10o to 12o angles of attack at various wind speeds (10, 15, 20, and 20 m/s). The normal blade showed an earlier stall at angle of attack at 10o. Additionally, the increase in wind speeds showed that the modified models did not exhibit better stall delay than the normal on then better performance than the normal model.