Numerical analysis of role of bumpy surface to control the flow separation of an airfoil

摘要

The efficiency of mission varying aircrafts can bealtered by either flow control method or adaptive wing technology. Here we haveresearched the control of the flow separation of airfoil by providing partialbumpy 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. Numericalapproach is undertaken to observe the flow separation on the aerofoil. From theobservation it was noted that by using the bumpy surface on the upper surfaceof 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 occursat 15 degree angle of attack.Thus, indicating the increase of lift force and control of flow separation of an airfoil due to bumpy surface.