Abstract
The efficiency of mission varying aircrafts can be altered by either flow control method or adaptive wing technology. Here we have researched the control of the flow separation of airfoil by providing partial bumpy on the upper surface of the geometry. Flow of low speed is considered. For the analysis purpose NACA 4315 was chosen. Two models were generated (i) regular airfoil using NACA 4315 profile (ii) providing bumpy surface on the NACA 4315 surface on the trailing edge at 80%C. Numerical approach is undertaken to observe the flow separation on the aerofoil. From the observation it was noted that by using the bumpy surface on the upper surface of the aerofoil the flow separation was delayed. Flow separation occurs at 9 degree angle of attack in the smooth surface whereas in bumpy surface it occurs at 15 degree angle of attack. Thus, indicating the increase of lift force and control of flow separation of an airfoil due to bumpy surface.
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