International Research Journal of Engineering and Technology (IRJET) e-ISSN: 2395 -0056 Volume: 03 Issue: 12 | Dec -2016 www.irjet.net p-ISSN: 2395-0072 © 2016, IRJET | Impact Factor value: 4.45 | ISO 9001:2008 Certified Journal | Page 985 Prediction of Turbulence Behavior over a 2D Double Wedge comparing K-Epsilon & K-Omega Model at Mach-4.2 Vamsi Krishna Chowduru 1 , Yashas C R 2 , Indraniil Roy 3 1 Assistant Professor, Department of Aerospace Engineering, IIAEM-Jain University, Bengaluru,India 2 Visiting Professor, Department of Aerospace Engineering, IIAEM-Jain University, Bengaluru,India 3 Visiting Professor, Department of Aerospace Engineering, IIAEM-Jain University, Bengaluru,India ---------------------------------------------------------------------***--------------------------------------------------------------------- Abstract - With a Steep Angle at the leading edge of Wedge a mechanical device which coverts velocities to higher shock waves and huge turbulence. Our current research work focuses on behavior of Shock waves expanding at the Wedge entry and exit. Predicting the flow behavior at various angles the Wedge behaves with huge change in lift and drag divergence at leading and trailing edge of the Profile. Estimating the Wedge transforming the velocity from its steep slope to the width. With specific design requirements for a gauge pressure of 200KPa and 4.2 Mach the behavior of Flow at various flow angle can be analyzed. For the estimation of K-Epsilon & K Omega over the wedge at Steep Entry Angle can affect the flow velocity consequently at intervals. Computational Fluid Dynamics tools over a solid wedge is being used to predict the behavior of the flow characteristics. Key Words: Steep angle, Wedge, Shock waves, K-epsilon, K- Omega, Flow Behaviour. 1.INTRODUCTION A Supersonic wedge is designed for carrying out Flow behavior Turbulence models. Our paper currently focuses on the Behavior of Flow over the Wedge with Steep edge angle for analyzing the past leading edge for Turbulent Kinetic Energy and Eddy Dissipation. Assuming the design input of Shock waves, deflection angle and angle β of the shock with respect to the inflowing gas. Depending on angle of the wedge the reaction of flow creates continuous dispersion of Flow across the surface of the wedge. A Solid wedge when is inclined at various angles the puzzling behavior of Flow will not remain streamline. With corresponding surface interaction of Oblique shock wave the straight shock emanates the flow subsequently onto the wedge width. A Wedge can experience high end impacts on large width area based on the span and Angle of attach. Each turn the supersonic flow makes can be computed separately from every other angle, no wave reflections back onto surface. Considering the Mach angle with respect to the geometry with an expression as The Propagation of Weak Disturbances and the coalescence into a Mach wave can be shown using predicted Flow Behavior. For a Mach value greater than 1 the transformation of Flow and Shock angles is determined as shown below 1.1 Flow Behavior From the edge of the Double Wedge surface the Leading edge experiences the immediate effect of velocity by which distribution of Flow is initiated. A Wedge can also experience Tangential velocity components based on the Mach number ahead in generating a shockwave. The Flow streamlines behind the shock are straight and parallel to the wedge surface. The Pressure of the surface of the wedge is constant and equal. Straight oblique shocks to the tip of the sharp edge in supersonic flow behavior in diverse relieving effect of surface. If the shock occurs from the same family of the flow the behavior seems to be intersecting and simply diverging.