CV: Aerospace engineer

 


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Candidate Profile
 Date Submitted:18-12-2011
 Last Modified:20-12-2011 (08:14)
Job information
 Current job:Aerospace engineer
 Employment Term:Permanent
 Job location:Own country
 Date available:immediately
 Industry:Consulting/Engineering Services
 Keywords
CV

Information                          Date of Birth: 04-10-1985

Objective                               Looking for a dynamic career which involves application of technical and analytical skills for solving practical aerospace problems.

Interests                                 Aerodynamics, Flight Mechanics & Control, Computational Fluid Dynamics, Experimental methods.

Education                             Institute of Aeronautical Engineering College, Hyderabad, India

                                                Masters Candidate, Aerospace engineering, 2009-2011(pursuing)Aggregate: 73.33 %

                                                Institute of Aeronautical Engineering College, Hyderabad, India

                                                B.Tech, Aeronautical engineering, July 2004 - May 2008, Aggregate: 65.26%

                                                Dissertation Topic: “Experimental studies on delta wing”

                                                Advisor: Prof. M. Anjaneyulu

                                                S.R Junior College, Warangal, India

                                                Completed HSC in June, 2003 with an aggregate of 72.30%

                                                Vani Vidya Vihar High School, Godhavarikhani, 2001 with an aggregate of  71.00%

Professional                          National Wind Tunnel Facility, Department of Aerospace engineering, IIT Kanpur.

Experience                            Project Associate                            22-may-2008 - 30-jun-2009

                                                Modelled space shuttle nose and launch-pad using CATIA V5 R16 for aerodynamic analysis. Also chimneys and cooling towers were modelled for aerodynamic analysis. The objective of these studies is to evaluate the aerodynamic loads (drag in particular) and moments in order to assess the performance of these structures.

Honours & Awards             Secured 2nd position in All India Hovercraft" competition - Shaastra 2007 held at IIT Madras.

Computer Skills                   Softwares: Lab View, AutoCAD, CATIA, MS Office, Tec plot, Ansys, Fluent and Gambit, Iron-cad, Mat- lab, ICEMCFD. CFD++

Operating Systems:             MS WINDOWS 98/2000/ XP/VISTA, LINUX

Relevant Coursework        

Technical Seminar-I                                            Technical Seminar-II

                                  (Experimental Investigation of an airfoil      (Study of Lee-Side Flows Over Conically

                                     at Low Reynolds number)                            Cambered Delta Wings at Supersonic Speeds)

                                                Undergone a course on Advanced CFD at Aeronautical Society of India, Bangalore 2011

                                                (Learnt about code writing on 2D grid generation and knowledge on writing NS solvers.)

Extracurricular

activities                                Participated in Aerodyne 2k6 in Aero Modelling category and got First prize.

                                                Participated in 58th International Astronautical Congress 2007.

                                                Participated in 17thUN/IAF Work Shop 2007 at NRSA Hyderabad.

                                                I am a Graduate Member of AeSI (The Aeronautical Society of India). G-11987

                                                Participated in AVIATION CONCLAVE 2010 at Hyderabad.

 

Dissertations:                       

TITLE:                  Experimental studies on delta wing (B.Tech)                         2008

Wind tunnel experiment has been initiated investigate the aerodynamic characteristics of 60deg.  sweep delta wing body model. The experiment was carried out in the 0.3m Trisonic wind tunnel at NAL Bangalore. The experiment was conducted at angle of attack was -6 deg. to 12 deg. and the Mach no was 0.8 M. Measurements are taken with six component strain gauge balance. The experiment showed that lift increase linearly till 5 deg. and then non-linearly from 5 deg. The slope of the pitching moment curve is positive. Due to vortex formation there is a sudden increase in slope at 5 deg. There is steep increase in the drag after 5deg. due to leading edge vortex formation.

 

M.Tech. Thesis    

 

TITLE: Prediction of High Angle-of-Attack Flow over Delta Wing body Configuration using CFD
Abstract
                The research effort investigates the flow field over a typical delta wing body configuration at high angle of attack. Delta wings with sweep angles of 60deg., 55 deg./60 deg and 50 deg./60 deg. with a bevelled  leading edge are modelled and simulated at a given Reynolds number (Re). Mach numbers are 0.5, 0.6, 0.7, 0.8, 8.85 and angle of attack is 0deg.to 22 deg.The flow simulations are carried out by the unstructured mesh with commercially available CFD++ used as N-S flow solver operating on hybrid grids. The unstructured hybrid meshes comprising of tetrahedral and prism elements are created by ICEM-CFD. HYENA is used to run the case here which is a Euler solver. The meshes are refined adequately to resolve the boundary layer flow. The aerodynamic characteristics are compared with the available experimental data. At low angles of attack, the aerodynamic characteristics vary in accordance with well-known linear aerodynamic behaviour.

Keywords: Delta wing, High AOA, CNS3D code, CFD++ solver, Grid generation, Aerodynamic characteristics.
 

External guides

Mr. Satya Prakash Sc-F  & Dr. K.P Singh
Aeronautical Development Agency (ADA), Bangalore.

 

References

1.       Prof.Dr.CVR Murthy      

2.       Prof.Dr.PV Subba Raju      -               pvsraju44@yahoo.co.in

3.       Prof.M.Anjaneyulu             -               anjaneyulum_hyd@dataone.in

 

 

DECLARATION

                I hereby declare that the above mentioned information given by me is true to the best of my knowledge.


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