Venkatesan D Email & Phone Number

Bengaluru, Karnataka, India

Involved in CFD projects related to Aerospace, Automotive and Electronics domain

Bangalore

• Design, development and CFD analysis of aerospace vehicles for in-house R&D projects The R&D activities include the design and analysis of full scale aircraft models, UAVs, airship, helicopter etc., The analysis (CFD) include geometry cleanup/simplification, grid generation, solution setup, post processing and report generation for various models as per the customer’s requirement. • The objective of these projects ranges from reducing the drag to increasing the range/endurance/stability of the vehicle • Aerodynamic shape optimization of airship (ecosat) Shape Optimization and Aerodynamic Stability analysis for Ecosat Airship was done for various configurations using CFD studies. Stability analysis is done by the estimation of aerodynamic forces and moments for alpha and beta sweep. CFD analysis were done for different hull shape, fin configuration, deflection etc. The results were validated through wind tunnel test data • CFD analysis of rear auxiliary propulsion system for A320. The objective is to perform CFD analysis of A320 fuselage to delay the boundary layer separation and generate additional thrust with the help of rear auxiliary propulsion system. CFD analysis to be carried out for different rear fuselage configurations to delay boundary layer separation. Steady state CFD simulations were carried out to estimate wall forces and coefficients using VBM approach in fluent• Drag reduction through boundary layer heating - UAV Boundary layer heating is done (through CFD modeling) at various span wise location on the wing to reduce skin friction drag component of the UAV• Analysis of various airfoil profiles for propeller design • Validation of wind tunnel test runs by performing CFD calculations • Hyperloop conceptual studies

Bengaluru Area, India

CFD simulation to evaluate aerodynamic forces and moments on LCA-Tejas and Mirage aircrafts.CFD analyses were done on different configurations of the aircrafts for various angle of attack and Mach number to evaluate aerodynamic co-efficients such as lift, drag and moment co-efficients which are used to estimate the performance as well as the trajectory of the aircraft/missile. The results are obtained using in-house flow solver and are validated against the experimental results/flight test data.CFD Study of a generic Wing-Pylon-Moving finned store: EGLIN test case. The objective is to establish the advantage of the in-house meshless solver over FVM & FDM. Quasi- static CFD analyses were performed on the geometry (Wing-Pylon-Finned store) to estimate aerodynamic loads which in-turn predicts the trajectory (Displacements & Euler angles) of the store. The CFD results are validated from the experimental data from AEDC, USA. A classic example of a moving body problem, the Eglin test case using the in-house solver, is validated.

Bengaluru Area, India

Aerodynamic load generation on LCA-Tejas for different configurations (inclusion and exclusion of various stores like Drop tanks, Bombs and Missiles) using PARAS 3D, which is a Cartesian grid based finite volume Euler solver.Aerodynamic forces and moments over various components of the aircraft are generated using CFD techniques in order to define load envelopes for the Light Combat Aircraft (LCA).CFD analysis of a mini UAV (for high endurance applications) to minimize drag. This project is focused on streamlining the fuselage of the UAV for various nose and tail configuration so as to reduce the total drag. This is done through the use of CFD tools such as ICEM CFD and Fluent. An optimized design of the fuselage was achieved through this CFD analysis.

Bengaluru Area, India

"Study of aerodynamic influence of radome on Airbus A380" This CFD study was performed to analyse the delta changes in the aerodynamic co-efficients due to the presence of a radome on Airbus A380 under AWACS (Airborne warning and control systems) India project."Drag estimation and aerodynamic design of an oblate spheroid using CFD tools such as ICEM CFD and ANSYS Fluent for AWACS India (Airborne Warning and Control Systems) project" In order to design this radome, the overall loads acting on it, i.e. aerodynamic and inertial loads, and the load distribution on the radome are required. The first step was to estimate the aerodynamic loads on the radome through numerical techniques. As a starting point, CFD tools are used to estimate the aerodynamic loads for different cases/configurations. The spheroid was analyzed for different aspect ratio and volume. The drag is estimated numerically and compared with empirical data which was used as a starting point in aerodynamic design. The design is further refined for minimal drag to provide aerodynamic efficiency

Master'S Degree, Aerospace, Aeronautical And Astronautical/Space Engineering, First

Bachelor'S Degree, Aerospace, Aeronautical And Astronautical Engineering, First Class With Distinction

Higher Secondary Certificate, Physics, Chemistry, Mathematics