A R V I N D H A K S H A N R A J A G O PA L A N S R I L AT H A

*** * *** **, *** #719 Phone: 408-***-****

San Jose, CA 95112 Email: abn66q@r.postjobfree.com

A E R O S PA C E E N G I N E E R

Aerospace Mechanical Automotive

• Self-motivated, enthusiastic and highly ethical Aerospace Engineer / Recent Graduate, with intern experience and

background in aerospace engineering, seeking to obtain engineering position at a company that values dedication and

hard work.

• Possess an inherent ability to excel at conceptual and logistical challenges; expert in analyzing data and resolving

problems. Highly motivated, fast learning, goal-oriented engineering professional with strong desire to share

analytical and technical skills; strong aptitude to acquire new skills and technologies while adjusting to new

environments.

• Excellent interpersonal and written and oral communication skills; able to maintain sight of the big picture and

succeed in challenging, deadline-driven environments. Able to work independently and as part of a team.

Education

Master of Science in Aerospace Engineering San Jose State University San Jose, CA (GPA 3.3/4.0) – 2012

Bachelor of Technology in Aerospace Engineering Amrita Viswa Vidyapeetham Coimbatore, India – 2011

Core Focus

Computer Aided Design

Low Speed Aerodynamics

Fluid/Aerodynamics Concepts

Project Management

Finite Element Concepts

Mechanical Design/Analysis

Solid Mechanics

Analysis/Problem-Solving

Electric Aircraft Design

Math / Science Background

Strong Work Ethic

Engineering Materials

Technology: CAD/ CFD/ Structural Analysis Software: CATIA V5, Solid Works, PRO E, AUTO CAD, GAMBIT/

FLUENT, ESI CFD, HYPERMESH/ABAQUS, MSC NASTRAN/PATRAN; Intermediate Certification in CATIA V5

Computer Skills: C, C++, MATLAB

CONFERENCE PRESENTATIONS

“MORE ELECTRIC AIRCRAFT” INTERNATIONAL CONFERENCE – BORDEAUX, FRANCE (NOV. 2012)

PRESENTED AT THE “MORE ELECTRIC AIRCRAFT” INTERNATIONAL CONFERENCE ON THE

DESIGN OF A 4-SEAT GENERAL AVIATION ELECTRIC AIRCRAFT WITH A MAXIMUM RANGE OF 800

KM. THE AIRCRAFT IS POWERED BY AN ELECTRIC POWER SYSTEM THAT COMPRISES OF A

BATTERY DRIVEN ELECTRIC MOTOR-PROPELLER SYSTEM. THE AIRCRAFT HAS A TAKEOFF

WEIGHT OF 1750 KG, AND A CRUISE SPEED OF 200 KM/HR.

Experience And Projects

Urban Airspace Technologies - Summer 2012

Aerospace Engineering Intern

Designed a state-of-the-art, remote-controlled floating signage display that is able to float in the air using an aerostat. Performed initial and final calculations and trade studies in order to design, develop and build this product. Using trial-

and-error methods to determine and execute the best way to build this product. Used CATIA V5 software to design and render images of the product.

CAD DESIGN & ANALYSIS PROJECTS – CATIA V5

COMPLETED THE FOLLOWING CAD DESIGN AND ANALYSIS PROJECTS USING CATIA V5

SOFTWARE:

• HARLEY DAVIDSON WHEEL DESIGN

• MOTORIZED CAN CRUSHER – DESIGN, MOTION ANALYSIS AND OPTIMIZATION

• MACHINE GUN – DESIGN, MOTION ANALYSIS, FEA AND OPTIMIZATION

ANALYSIS OF BALLISTIC IMPACT ON COMPOSITE PLATES

MODELLED A PROJECTILE AND COMPOSITE PLATE IN HYPERMESH. USED KEVLAR 29–EPOXY AND

KEVLAR 49–EPOXY MATERIALS AND USED 2-D SHELL ELEMENTS FOR MODELLING. THE EDGES OF

THE PLATE WERE FIXED. AK-47 BULLET WAS USED AS THE PROJECTILE. THE STEEL BULLET WAS

MODELLED WITH 2-D SOLID ELEMENTS AND INPUT WITH A PROJECTILE VELOCITY OF 700 M/S.

THE STRESS/FAILURE ANALYSIS WAS PERFORMED ON THE COMPOSITE PLATE AT FIVE

DIFFERENT PLY ORIENTATION ANGLES USING THE ABAQUS SOLVER.

ANALYSIS OF RIBS AND SPARS OF AN AIRCRAFT WING

RIBS AND SPARS OF A TWO-SEATER GENERAL AVIATION AIRCRAFT WERE DESIGNED IN CATIA AND

STRESS ANALYSIS WAS PERFORMED IN MSC NASTRAN/PATRAN. THE SHAPE OF THE RIB WAS

BASED ON AN NACA 0012 AIRFOIL. THE RIB STRUCTURE WAS OPTIMIZED; CUT-OUTS AND

FLANGES WERE OPTIMIZED BASED ON THE STRESS ANALYSIS RESULTS. USED AN I-BEAM SPAR TO

PROVIDE CONCENTRATION TO KEY LOADING POINTS DUE TO MAXIMUM BENDING RESISTANCE

TO WEIGHT RATIO.

DESIGN, MANUFACTURE AND ANALYSIS OF A FINITE WING

CONSTRUCTED A FINITE WING WITH WOOD OUT OF AN NACA 23018 AIRFOIL WITH NO SWEEP.

PERFORMED WIND TUNNEL TESTS ON THE WING AT DIFFERENT ANGLES OF ATTACK. THE

RESULTS WERE COMPARED WITH THE CFD RESULTS.

DESIGN, MANUFACTURE AND ANALYSIS OF AN AIRCRAFT WITH MAXIMUM PAYLOAD CAPABILITIES

DESIGNED AND CONSTRUCTED A MODEL AIRCRAFT WITH MAXIMUM PAYLOAD CAPABILITIES

USING WOOD. PERFORMED A SURFACE FLOW VISUALIZATION IN A LOW SPEED WIND TUNNEL

WITH A FLOW SPEED OF 30 M/S. FLOW DATA WAS MEASURED USING PIVOT TUBES THAT WERE SET

UP THROUGHOUT THE SURFACE OF THE MODEL AND COMPARED WITH THE CFD RESULTS

OBTAINED FROM GAMBIT/FLUENT.

SONIC BOOM MITIGATION BY AIRCRAFT NOSE CONE MODIFICATION

THE SONIC BOOM INTENSITIES OF FIVE DIFFERENT AXISYMMETRIC AIRCRAFT NOSE

GEOMETRIES WERE STUDIED THROUGH ANALYTICAL METHOD AND CFD ANALYSIS. THE NOSE

GEOMETRY WAS MODELLED USING SOLID WORKS. THE CFD ANALYSIS WAS PERFORMED USING

ESI CFD TO FIND GEOMETRIES OF LESSER DEFLECTION ANGLES PRODUCING A RELATIVELY

LESSER SONIC BOOM.

CFD ANALYSIS OF AIRFLOW WITHIN THE FRONT WHEEL CAVITY OF AUTOMOBILES

PERFORMED 2-D AND 3-D FLOW ANALYSES OF FRONT WHEEL CAVITY OF A CAR USING

GAMBIT/FLUENT WITH A ROTATING BOUNDARY CONDITION SPECIFIED FOR THE WHEEL.

RESULTS INDICATED DRAG PRODUCED IS PROPORTIONAL TO THE SIZE OF THE CAVITY.

DESIGN OF AN AERIAL FIRE FIGHTING VEHICLE

DESIGNED AN AERIAL FIRE FIGHTING VEHICLE THAT WILL REPLACE THE FLEET OF AIRCRAFT

CURRENTLY IN OPERATION. IT IS A TWIN ENGINE AMPHIBIOUS AIRCRAFT WITH A TWIN TAIL

BOOM EMPENNAGE THAT IS DESIGNED TO CARRY A PAYLOAD OF 12,500 LBS. THIS WILL ENABLE

A R V I N D H A K S H A N R A J A G O PA L A N S R I L AT H A Page 4

AN AIRCRAFT TO CARRY 1,200 GALLONS OF WATER OR FIRE RETARDANT.

CFD ANALYSIS OF A SUBSONIC JOINED WING AIRCRAFT

MODELED A JOINED WING AIRCRAFT IN SOLID WORKS. CONDUCTED ANALYSIS USING ESI CFD IN

3 STAGES: WING TIPS, WINGS AND INTERACTION BETWEEN WING AND FUSELAGE. THE RESULTS

WERE OBTAINED TO VERIFY INCREASED AERODYNAMIC PERFORMANCE, INCREASED WING

STRUCTURE SUPPORT, HIGH MANOEUVRABILITY AND STOL ABILITY.

DESIGN AND CFD ANALYSIS OF THE COMBUSTION CHAMBER OF A ROCKET ENGINE

DESIGNED THE COMBUSTIÓN CHAMBER OF A ROCKET ENGINE BASED ON THE THRUST

REQUIREMENTS OF THE ROCKET. THE COMBUSTIÓN CHEMISTRY WAS STUDIED AND THE EXACT

DIMENSIONS OF THE CHAMBER WERE OBTAINED. AN ADAPTABLE CAD MODEL WAS DESIGNED

USING EQUATIONS IN SOLIDWORKS. THE COMBUSTIÓN PROCESS WAS SUCCESSFULLY MODELED

IN CFD, USING ESI CFD, BY SPECIFYING THE EXACT REACTION MECHANISM AND THE INITIAL

CONDITIONS.

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