Numerical Analysis of Incompressible Low-Re Impulse-Flow Over Staggered 2D Circular Cylinders Yagneshkumar A Joshi, Ramesh Bhoraniya, and Harichandan A B Seventh Sense Research Group Journals - Cylinders are essential in constructing several engineering designs where fluid passes over them. Under varying environmental conditions, the fluid flows with impulse, affecting design structures considerably. This paper presents the numerical analysis of incompressible low-Re gusty flow with impulse inlet passing through three staggered cylinders. The problem is numerically simulated and investigated for two distinct variable factors keeping one constant at a time: inlet gust frequency and Reynolds number. The vorticity contours are obtained that provide information about local rotation. The streamlines are obtained to identify the wake region. The C L , C D, and St are computed. The results show a beneficial effect of variability in impulse intake velocity on the wake region generated between and behind the cylinders. It represents enhanced flow characteristics derived from low angular gust frequency value of intake velocity fluctuation.
Design Analysis of a Blended Wing Body Pushpal Das, Prince Roy Sharma, Rama Krishna Parida, Ayush Pradhan, Aayush Nanda, Pooja Chaubdar, and Atal Bihari Harichandan Springer Nature Singapore
Low Reynolds Number Flow Past Square Cylinder in the Vicinity of a Plane Wall Biranchi Narayana DAS, Manoj UKAMANAL, and Atal Bihari HARICHANDAN INCAS - National Institute for Aerospace Research Elie Carafoli The characteristics of flow over a square cylinder in the vicinity of a plane stationary wall have been numerically investigated. 2D time-dependent incompressible flow at low-Reynolds numbers of 100 and 200 has been calculated using the finite volume method. CFRUNS scheme is used for pressure-velocity coupling in numerical calculation. The authors have tried to make an attempt to analyze the features of the complex flow field through flow streamlines and the vorticity contours. The impact of the gap between the cylinder and the plane wall upon flow pattern behavior is also studied. An intense interaction between vorticity in the boundary layer generated over the plane wall and the vorticity associated with the shear layer emanating from the separation points on the cylinder surface has been observed producing a very complex flow field in the cylinder wake and the gap between the cylinder and the wall.
Adjoint Based Optimization of NACA 4412 Airfoil Biranchi Narayana Das, Manoj Ukamanal, and Atal Bihari Harichandan IEEE In this research paper, the shape optimization of the NACA 4412 airfoil has been carried out at 00 angle of attack and stall angle of attack, at moderate Reynolds number. The NACA 4412 airfoil has been used in sports planes which have a higher cruise speed compared to cargo planes. Hence, the shape of the airfoil needs to be optimized for achieving a higher lift to drag ratio. The adjoint method has been used to optimize the shape using ANSYS Fluent software.