Pradhani - CATIA V5, CFD - Chennai, TN, India

Nagapp Pradhani

Chennai, TN, India

Services

CATIA V5, CFD

Summary:

 ANSYS(ICEM CFD, ANSYS CFX, FLUENT), HYPER MESH,
NASTRAN-PATRAN.

Work History

ACADEMIC PROJECT

January 2013 - May 2013

Project Title: "DESIGN AND OPTIMIZATION OF UAV WINGLET".
This project involves modeling and numerical analysis of UAV wing. In this work we analyzed Grid independence study, Iterative convergence studies, Turbulence Model testing and after validation with experimental results we optimized is Blended winglet by varying Different cant angles, Taper ratio. Lift coefficient is enhanced by 26.17% for Taper Ratio 0.7 with cant angle 400 of a Blended winglet and drag is reduced by 13.81 %. It is also observed that L/D of a Blended winglet is increased against base wing by 46.448%. This drastic increase in lift to drag ratio is due to reduction in induced drag and increase in lift of a base wing.

Tr. Content Analyst

In-Plant Training in HAL

From January 2012

" at Griha Software Technologies Pvt. Ltd.
❖ Project Student in Indian Institute of Science (IISc) Bangalore

Team Leader

July 2012 - July 2013

Responsibilities: The process involves Modeling the Geometry using CATIA V5, Cleaning Up the model using ANSYS ICEM, Generating good quality Grids on the cleaned up model. Checking up of mesh quality, aspect ratio, Skewness and its improvisation. Generated mesh were Simulated using CFX with required boundary conditions and Post Processing are done with CFX-POST, and analyzing with theoretical flow physics.


❖ PROJECT: 1
This project describes modeling and numerical analysis of UAV wing with NACA 653-218 airfoil. Project titled "NUMERICAL INVESTIGATION OF UAV WING AND REDUCTION OF DRAG USING WINGLET OPTIMIZATION". The design is analyzed and has been validated with the Experimental results using unstructured grid and run with Navier stokes code, now working on improvisation of the wing L/D by using winglet ("Inverted L" winglet), The same aerofoil is used for the design of Inverted "L" winglet Different cant angles, Taper ratio, horizontal distance and angles of "Inverted L" winglet is considered for optimization and these optimized results are compared with the base wing.

Qualifications & Certifications

Engineering

Visvesvaraya Technological University

Karnataka State Secondary Education Board

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