Corresponding Author: Vipul Namdev 12 Email address: Vipulnamdev1995@gmail.com Copyright ©ijrei.com International Journal of Research in Engineering and Innovation Vol-1, Issue-1 (2016), 12-19 _____________________________________________________________________________________________________________ International Journal of Research in Engineering and Innovation (IJREI) Home page http//: www.ijrei.com ______________________________________________________________________________________________________________ Analysis of Vortex Formation around a Circular Cylinder at low Reynolds Number Vipul Namdev, Prashant Kumar, Ashish Tyagi, Kartik Kumar Graduate Student, Department of Mechanical Engineering, Meerut Institute of Technology, Meerut, India _________________________________________________________________________________ Keywords Reynolds Number, Lift coefficient Drag coefficient Circular Cylinder Angle of attack Abstract Vortex shedding is one of the most interesting phenomenon in turbulent flow. This phenomenon was first studied by Strouhal. In this paper, the analysis of vortex shedding around a 2 dimensional circular cylinder with Reynolds No of 200, 500, and 1000 with different angle of attack 0 0 , 5 0 , and 10 0 has been studied. In this simulation an implicit pressure-based finite volume method and second order implicit scheme is used. Flow has been studied with the help of Navier-Stokes and continuity equations. The pressure, drag coefficients and vortex shedding for different Reynolds numbers and different angle of attack were computed and compared with other numerical result that show good agreement. © 2016 ijrei.com. All rights reserved __________________________________________________________________________________ 1. Introduction The effect of the flow over a rotating cylinder at high rotational rates. 12 rotational rates from 0 to 8 are examined at 3 Reynolds number, Re = 5 ×10 5 ,10 6 and 5 ×10 6 . This study shows that the lift and drag force varies slightly in the Reynolds number range (less than 10%). Lift increases linearly with spin ratio (a) and the drag force increases up to a = 4, where it reaches a plateau and eventually decreases. [1]. Investigate high Reynolds number flow (1×10 6 , 2 ×10 6 , 3.6 ×10 6 ) around a smooth circular cylinder by using 2D URANS equation with a standard K-epsilon turbulence model for engineering applications in the supercritical and upper-transition flow regimes was examined in this research. The essential hydrodynamic quantities such as coefficient of drag, lift and strouhal number predictions shows acceptability of the data. The computed cd and skin friction coefficient decrease slightly as the Reynolds number increase [2]. The deflection is increased when we increased the Reynolds Number with increase their angle of attack The maximum deflection occur in Re-1000, angle of attack 15 0 i.e. 9.2597x10 -3 mm and minimum value of deflection occurs in Re-100 with angle of attack 0 0 i.e.1.4618 x 10 -4 mm. the highest natural frequency 34.353 Hz was found in mode 6 which is torsional mode, whereas minimum natural frequency 0.6951 was found in mode [3]. The time-averaged lift and drag generation of two flexible membrane wings with different skin flexibilities (flexible nylon and flexible latex wings) are compared with those of a rigid wing.The effect of the Reynolds number on the gliding ratio is that at Re 1000 and at angle of attack (here after, AOA) 15 0 , the largest gliding ratios are obtained. Flow invariably for all Reynolds number, minimum Drag coefficient is obtained at AOA 15 0 [4] It was found that for all the simulations performed flow always remained steady at Re 100 and 200 at all angle of attack (0 0 to 15 0 ). First unsteady flow was obtained at Re 500 and AOA 10 0 . But flow always remained steady at AOA 0 0 and 5 0 for all the Reynolds numbers [5]. The mean drag coefficient is under predicted by this method for a wide range and strouhal number is over predicted. The length of separation bubble predicted shown