Mar 2016 – Nov 2016 · 8 mos · Brussels Area, Belgium

• Unsteady Analysis of the NREL Phase VI Wind Turbine using Non-Linear Harmonic (NLH) Method
• This thesis has presented a novel approach of CFD modeling of wind turbines using a turbomachinery approach by means of Non-Linear Harmonic (NLH) method. This reduced-order frequency domain CFD approach allowed to drastically reduce the required computational time of unsteady simulations. The study was based on the Horizontal Axis Wind Turbine (HAWT) model published by the National Renewable Energy Laboratory (NREL) and it was demonstrated that the unsteady NLH computations reduced the computation time of wind turbine simulations by two order of magnitude compared to traditional URANS approach.

Nov 2015 – Feb 2016 · 3 mos · Poitou-Charentes, France

• Unsteady Potential Flow as a Source of Sound
• The aim of the project was to extract the potential part of the flow over bluff bodies.The focus was on decomposing the provided flow field (unsteady velocity field) into longitudinal (diverging, non-curling, irrotational) vector field and a transverse (solenoidal, curling, rotational, non-diverging) vector field. A numerical setup was designed in MATLAB® and applied to the existing databases, both for a selection of body flows and for free shear flows so that the potential flow can be analysed from an acoustic point of view.

Apr 2015 – Aug 2015 · 4 mos · Lille Area, France

• Turbulent Structure Detection and Characterization of Large Scale Motions (LSMs) in Outer Layer
• The focus of this project was on analyzing the PIV data by means of image processing toolbox of MATLAB®. An efficient technique using Gaussian filter is used to clean the noise from raw images (obtained from PIV experiment) without changing the statistics of turbulent structures significantly. The motive was to detect regions of stream-wise negative velocity fluctuations (u') and provide new insight about the role of the large scale motions in the turbulent boundary layer. The shape measurements (such as length, aspect ratio, and area etc.) of these turbulent structures were also performed to characterize them.

May 2013 – Oct 2013 · 5 mos · Germany

• Onsite assignment for special projects.

Dec 2010 – Aug 2014 · 3 yrs 8 mos · Bangalore,India

• I was associated as a Sr. CFD Engineer with CSM Software Pvt Ltd, India, which has been a pioneer in the area of CAD/CAE/CFD solutions for the Automotive, Aerospace and Defense Sector across the country. My association with this company has given me about 4 years of solid work experience in the field of CFD.
• I also provided offshore support as a project coordinator for European and American customers and lead a team of 4 CFD engineers.

Dec 2009 – Mar 2010 · 3 mos · Bangalore, India

• Computational Investigation of Staged Fuel Injection In A Supersonic Stream
• The design of a supersonic combustion ramjet (scramjet) combustor requires very efficient fuel–air mixing methods because of the short residence time of airflow within the engine. Therefore, rapid mixing between the fuel and air is required, while minimizing the stagnation pressure loss. Transverse injection of fuel in a supersonic stream is a widely investigated approach as it provides rapid fuel–air mixing and rapid penetration of the jet into the airflow. A baseline CFD approach using the commercial code FLUENT was developed and validated by comparison with the experimental work of Eklund et al on staged transverse injection into a supersonic flow to compare the predictions of CFD results with experimental data and a reasonably fair agreement was obtained for the major features of the flow. Special emphasis was laid on developing a rigorous good quality mesh for the domain with a boundary layer mesh along the wall which resulted in a average wall y+ of 1.38, this was complemented along with a dense mesh around regions near the injector which became progressively coarser moving away from the injector region. Two popular RANS models, SA model and the K-w SST model for compressible flow were used and a reasonably good agreement was obtained both for the overall flow field and with the pointwise LIIF/LDA measurements Using this methodology , the mixing of hydrogen in free stream for the same geometrical configuration with an angled injection was studied. Contour plots of mole fraction of hydrogen at various sections of the combustion chamber were obtained to qualitatively investigate the mixing process.

Jun 2009 – Jul 2009 · 1 mo · Hyderabad Area, India

• Calculation of Aerodynamic Characteristics of NACA 2415, 23012, 23015 Airfoils Using CFD
• A method of solving the flow over airfoils of NACA (National Advisory Committee for Aeronautics) series - 2415, 23012 & 23015 is proposed using the assistance of commercial CFD packages Gambit and Fluent. The solution was obtained by solving the steady-state governing equations of continuity, momentum, and energy conservation combined with standard k-w turbulence model. NACA airfoils with angle of attack from -15 to +15 degrees with an interval of 5 degrees were analyzed. Calculations were made for constant air velocity altering only the angle of attack for each airfoil.