NAVEEN V PATIL

OBJECTIVE

M.I.G-**, *st main, near Vijaya Bank ATM,

Navanagar, Hubballi Karnataka.

Pin code: 580025

+91-701*******

addnnh@r.postjobfree.com

An Aerospace Engineering graduate with strong fundamentals in aerodynamics, aerospace propulsion, Aerospace structures, fluid mechanics, thermodynamics and CFD analysis and have qualified GATE 2020. Looking forward to an opportunity in the design and analysis domain while fulfilling organizational goals.

EDUCATION

B.Tech in Aerospace Engineering IIAEM, Jain University, Bengaluru 2013 – 2017

Aggregate: 74.81%

Pre-University Vidyaniketan Science PU college, Hubballi 2010 – 2012

Percentage: 76.50%

10

th

Std. NREM School, Hubballi

2009 – 2010

Percentage: 88.00%

GATE 2020 Score 482

Advanced course on CFD analysis Niharika Institute of Computational Engineering, Bengaluru.

DEC 2017-MAR 2018

SKILLS

CATIA V5 ANSYS CFX

SOLIDWORKS ANSYS ICEM CFD

ANSYS FLUENT

WORK EXPERIENCE - CFD Freelancer(1 Year)

Worked on CFD consultancy projects at NICE, Bengaluru. Involved in cleaning up the CAD model, meshing, and mesh quality check, setting up the problem and running the case.

Worked (freelancing) on various CFD mini projects for students and Ph.D. fellows. PROJECTS

Design and fabrication of SWASHPLATE ASSEMBLY, HELICOPTERS (Final year project) The main objective was to illustrate the basic function of cyclic and collective pitch control inputs with a conventional rotor head. Designed the swash plate assembly (helicopter) without taking loads into account by trial and error method. Fabricated the same using Aluminum and Nylon material. Aluminum material for the rotating swashplate, fixed swashplate, shaft and rotor head. Nylon material for the spherical ball along with aluminum bush. Ball housing with nylon.

CFD analysis of incompressible flow over aerofoil Aerodynamics analysis on aerofoil by K-epsilon, Spalart Allmaras, and K-Omega methods. The main objective was to calculate coefficient of lift and coefficient of drag and to compare the results by plotting angle of attack vs CL and angle of attack vs CD. Results close to experimented results were found by Spalart Allmaras and K-Omega methods.

CFD analysis of subsonic diffuser of turbojet engine afterburner The main objective was to estimate the pressure drop and flow development (deswirling) through the diffuser. The turbine is rotating machinery, and turbine exit is a high degree swirling flow. Airfoil struts are used as flow deswirling structures. Conducted CFD analysis and calculated total pressure, total temperature, Mach number and swirl angle at the outlet. It was found that the swirl angle was decreased.

DECLARATION

I, Naveen V Patil, declare that the above information is true to the best of my knowledge. Date:

Place:

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