1. RAJARAMAN.A.S
14, Murugaya thottam,
K. Parai Patty, Dindigul ,
Tamil Nadu - 624002, India.
EMAIL: aeromailrajaraman@gmail.com
CONTACT NO: +91-8220102676,7795721475
D.O.B: 08-05-1990
OBJECTIVE
To become a successful professional in the field of engineering and to work in an innovative
and competitive environment which utilizes my skills and abilities.
EDUCATION AND QUALIFICATION
Course Name of Institution Year of
Study
Percentage
of Marks/CLASS
BE
(AERONAUTICAL)
Hindustan Institute Of
Technology & Science,
Chennai.
2008-2012 66.5%
12th
standard
IDEAL Higher Secondary School
, Erode, Tamil nadu 2007-2008 71.25%
10th
standard
IDEAL Higher Secondary School
, Erode, Tamil nadu 2005-2006 85.5%
WORK EXPERIENCE
CADD ZONE (Bangalore): 08/2013 to 01/2015
 Teaching AutoCAD for Mechanical, Electrical, Civil, Architectures and Interior
Designers.
 Teaching CATIA and Unigraphics NX for Mechanical, Automobile, and Aeronautical
Student’s.
TECHNICAL SKILLS
 Design Software: Proficient working knowledge in Auto CAD, CATIA V5 R20, Pro-E
and Unigraphics

2.  Meshing and Analysis: Basic working knowledge in ANSYS fluent, Workbench and
CFX
COMPUTER SKILLS
 Proficient in technical documentation using Microsoft Word.
 Good Presentation skills using Microsoft PowerPoint
 Tabulations and Graph using Microsoft Excel
TECHNICAL ACHEIVEMENTS
 Achieved first place in paper plane design at State level Tech. fest at VELTECH
Engineering College, Chennai.
 Volunteered 6th
NATIONAL CONFRENCE on AUTOMOTIVE INFOTRONICS
towards Intelligent, Connected and Green vehicles in ANNA UNIVERSITY Chennai
(SAEINDIA-2010 Dec17, 18).
 Secured second prize in Auto Quiz (SAEINDIA Student convention-Sep2010).
 Participated in RC BUILD FEST 2010 conducted by Rotor sports & Hobby Pvt. Ltd.
KEY PROJECTS
1. COMPUTATIONAL ANALYSIS OF FLOW SEPARATION IN A DE LAVAL NOZZLE
 The objective of this study is to clarify flow structure inside and outside of a rocket
nozzle, which are indispensable for actual development of rocket nozzle design. The
study is motivated by the flow separation occurring inside C-D nozzles operated at low
pressure ratio.
 It analyses the basic flow structures that may take place inside and outside the nozzle
divergent section during the start up and the low altitude flight, when nozzles operate in
over-expanded regime.
 The model was designed using Gambit and flow simulations were carried for the two-
dimensional convergent-divergent nozzle using ANSYS Fluent.
 Results from this study indicate that off-design over-expanded nozzle flow was
dominated by shock induced boundary layer separation, which was fully detached two-
dimensional separation flow downstream of the shock. Flow accelerates to supersonic
speed and then recompresses.
2. Completed Aircraft Design Project on ‘Military Cargo Aircraft’.
3. Design and fabrication of RC Aircraft.
4. Design and fabrication of a RC Tail less glider.

3. LANGUAGE SKILLS
 English: Proficient (Read/Speak/Write)
 Tamil: Proficient (Read/Speak/Write)