A dynamic, innovative, performance driven and highly motivated CFD engineer with more than 6+ years of experience in fluid dynamics, thermal system, Gas turbine design and analysis. Excellent problem solver with effective management, leadership qualities, learnt skills and acquired knowledge to build a career, which is intellectually challenging and personally rewarding.

       As CFD analyst in ICEM CFD, FLUENT.

Ø  Hands on experience in simulation soft wares such as fluent. 6.5, ICEM CFD .10.           

Ø  Development of geometry, surfaces, parts and blocking for varying scale of meshing.

Ø  Experience in tetra, hexa, prism, structured and unstructured meshing.

Ø  Experience and knowledge on grid generation, fines, skew ness, aspect ratio, cell orientation of faces and grid topology.

Ø  Experience and knowledge in setting of simulation type of steady, transient and turbulence model,

Ø  Knowledge and experience for setting of boundary flow field condition and physical domain setting, moving boundary analysis.

Ø  Knowledge of solvers for steady state problem, transonic flow and turbulence model.

Ø  Knowledge on multi-grid convergence acceleration method, second order spatial discretisation.

Ø  Experience and knowledge in sources of errors and its correction techniques.

Ø  Experience and knowledge in post processing techniques.

As analyst in CFX blade gen10 turbo machinery /ax stream

Ø  Experience on blade modular design of turbo mechanics geometric property of hub, shroud, tip, theta periodic, curves of inlet, and outlet mean line design.

Ø  Knowledge in defining the control angle between inlet and axis of rotation and periodic surfaces.

Ø  Experience and knowledge in setting the grid generation topology.

Ø  Knowledge in defining the range of one on one periodicity by interface.

Ø  Knowledge in choosing the apt type of grid, near wall and smoothening technique.

Ø  Experience in generating 3-d mesh for blade profile.

Ø  Knowledge in defining the layers between hub and shroud.

Ø  Knowledge in editing master control points and defining mesh static parameter

Ø  Experience in solver control of blade gen 10 in CFX, calculation of inlet and outlet velocity, flow angle by Velocity triangle method.

Ø  Experience in post processing technique of velocity vector analysis, flow in iso surfaces and path line of flow.

Experience in gas turb 11 soft ware /NLR. (Performance analysis)

Ø  Experience in aircraft cycle analysis, engine component, flight propulsive efficiency

Ø  Experience in using matlab, simulink on development, maintenance of gas turbine cycle model for steady, transient performance prediction.

Ø  Understanding of component performance characteristic maps and their representation in cycle model.

Ø  Parametric  design using gas turb 11 for analysis of higher cycle efficiency using two spool, fan with two stage compressor for various input constrains

Ø  Experience in use of compressor, turbine working contour map in iterating surge margin%, Reno correlation, bleeds handling.

Ø  Off design analysis of spool speed with control operating points, iterations for convergence of beta value and auxiliary loads in finding flow speed at design point, corrected speed and mass flow, nozzle area.

Ø  Basic knowledge in using geometry editor of gas turb11 in designing general engine configuration ,inlet design, compressor design, flow annulus shape, blade stage,  burner, std convergent nozzle, bypass ratio and shape, etc in meeting cycle constraints .

 Experience in aero design soft wares x-foil, XFLR4.

Ø  Knowledge in defining aerofoil model parameters such as thickness, chamber, max pt, by B-spline, splined pts, interpolation, inverse method.

Ø  Knowledge in defining polar objects such as angle of attack, Re,M,laminar to turbulence transition criteria, etc

Ø  Significance of operating pts in series of inlet (bl) input data and convergence with sequential analysis.

Ø  Knowledge in defining wing body by its length, root to tip chord, leading edge offset, dihedral angle etc

Ø  Experience in polar mesh type on panels I order, II order with the association of vortex and doublet source to each panel.

Ø  Viscous and in viscid calculation of LLT, over VLM, 3D panel method by interpolation.

Ø  Knowledge in optimization technique MDO in designing and air craft simulation.

 The project work is to carry the analysis and to study the criterion for the flow separations in a convergent-divergent nozzle .To determine the point of flow separation in c-d nozzle. The various phenomenons of sub sonic, Tran’s sonic, super sonic, normal and oblique shock formation are observed. The optimum condition of exit pressure for over expansion, under expansion and optimum expansion is also determined. The computational data are compared with Schumacher’s criterion, Summerfield criterion. Schilling curve.

Boundary conditions:

v  Reynolds numbers of the nozzle flow is Re 10⁶ with a favorable pressure gradient. Therefore, the viscous effects may be ignored as a first approximation.

v  The ratio of exit area and throat area is four; the corresponding pressure ratio from theoretical calculation is 33.56. So in the computation work the inlet total pressure is taken as 33.56 bar and the exit pressure is varied.

v  The computation is done using the FLUENT software involves solution of the Navier-Stokes equation for the flow with a built in k-ε turbulence mode

 CFD analysis of external aero dynamics, calculation lifts drag and other flow coefficient analysis for different velocity and Reynolds no. Minimizing formation of vertex, closer towards stream lined flow.

Parametric design using gas turb11 for analysis of higher cycle efficiency using two spool, fan with two stage compressor for various input constrains

Preparing compressor and turbine maps, matching turbine with compressor maps for load and flow coefficient.

 A Generic aero thermal model was created with 1-D non linear un-steady governing equations representing aero thermodynamic process of each engine component .The engine performance characteristics such as specific fuel consumption, component pressure ratio, thermal and propulsive efficiency are analyzed with transient condition by changing the fuel flow rate with time.

I have rich experience in moving boundary problem analysis, turbo charger, fan, gas turbine engine design, analysis and optimization

PROJECT TITLE:  comparison of effectiveness of s1223 and   NACA6412 air foil for MAV 

      At low Reynolds number.

    An aero foil design best suitable for micro air vehicle was analyzed with its varying phenomenon for area ratio, low Reno, pressure distribution and free stream turbulence.

A thin air foil of low AR wing design of s1223, 12% thickness, 8%camber was chosen, a wooden wing was made. Comparison Cl, Cd, Cm, and LD for various Re.no, AR, and 3D- flow effect was made with that of air foil model NACA6412 for same Re.no of the order of 10⁵ and varying the angle of attack.

  Date of birth              :           20-09- 1981

  Sex                            :           Male

  Marital status              :           Single

  Languages known       :           English, Tamil.

  Nationality                   :           Indian

Declaration: 

             I  hereby   declare  that  all  the  information  given  in  this document is true to the best of my knowledge.