International Research Journal of Engineering and Technology (IRJET) e-ISSN: 2395-0056 Volume: 05 Issue: 06 | June 2018 www.irjet.net p-ISSN: 2395-0072 © 2018, IRJET | Impact Factor value: 6.171 | ISO 9001:2008 Certified Journal | Page 1009 SUBSONIC FLOW STUDY AND ANALYSIS ON ROTATING CYLINDER AIRFOIL Abhishek Sharma 1 , Tejas Mishra 2 , Sonia Chalia 3 , Manish K. Bharti 4 1, 2 Student, Department of Aerospace Engineering, Amity University Haryana, Haryana, India 3, 4 Assistant Professor, Department of Aerospace Engineering, Amity University Haryana, Haryana, India ---------------------------------------------------------------------***--------------------------------------------------------------------- Abstract - The concept of moving surface- boundary layer control is explored in this paper. A planned study was carried out on a conventional symmetrical airfoil 0012, of 100mm chord length. The study was complemented by numerical analysis and Computational fluid dynamics analysis through simulation. The moving surface was provided by rotating cylinder, located at C/8 and C/4 (where C is the chord length) distances from the leading edge. The diameters taken for the case were 13mm and 15mm respectively. The presence of rotating cylinder in a 0012 affects the airfoil lift characteristics. It provided the proper pressure variation and hence the lift at zero degree of angle of attack. Rotating cylinders at both the locations resulted in a significant increase in the lift through momentum injection by 100% and delayed the stall characteristics. Nomenclature: = Coefficient of drag = Coefficient of lift D = Aerodynamic drag Force L = Aerodynamic lift force C= Chord length of airfoil d = diameter of cylinder t = maximum thickness of airfoil r = radius of cylinder = angular velocity of rotating cylinder = Free velocity of air = Total velocity at any point (x, y) , = Velocity in x & y direction respectively Re = Reynolds Number = Static pressure q = dynamic Pressure Ø = Velocity Ratio/ Factor = Kinematic viscosity of fluid (air) = 1.729 × 10 5 Kg/ms α = Angle of attack ȋAOAȌ = Density of air = 1.225 kg/ 1. INTRODUCTION An airfoil is a basic element, which define the amount of lift and drag can be generated by a wing of an aircraft. As the airfoil is the basic key for lift generation. Thus enhancement in the design of an airfoil can also improve the lifting characteristics. The major theory behind the generation of lift over an airfoil is that, when a flow passes over a surface of an airfoil a pressure difference is generated due to which lift is generated. For positive lift generation i.e. upward force the pressure over the upper surface has to be low compare with lower surface of an airfoil [1]. This pressure gradient or difference is made, either by varying AOA in symmetrical airfoil or by using camber airfoil. Mainly the airfoilǯs designing is done by observing the changes in parameters like lift, drag, pressure, temperature, velocity etc. at its surface. These changes has been observed at different air velocities and at different angle of attack. 1.1 Magnus Effect When a side force is generated on a rotating cylinder or solid sphere immersed in a fluid (mainly air) due to its relative motion between the rotating body and the fluid. This phenomenon is known as Magnus effect [2]. By using. This principal is also work behind the working setup of Anton Flentterǯs rotating cylinder or Flettnerǯs rotor. This defines that a rotating cylinder is able to generateǯs lift by creating pressure differences over its surface (as shown in Fig 1 [3]) by following Magnus effect principle. Fig -1: Rotating Cylinder (Sketch of Magnus effect with streamlines by Rdurkacz) The airfoils which are the typical combination of both conventional and rotating cylinders (as shown in Fig 2 [4]). can be defined as complex airfoils or rotating airfoils. This study is also based on these type of airfoils.