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CFD Simulation of an Airfoil at different Angle of Attack

Authors(3):

Mragank Pratap Singh, Dr. Mahendra Singh Khidiya, Sahil Soni
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This research describes simulation of computational fluid dynamics (CFD) problems that occur in physical practices. The primary focus is on the simulation of the airflow around the airfoil. The fluid flow simulations are obtained with the FLUENT software package of ANSYS. The  model was prepared with the software SOLIDWORKS. The preprocessing includes the creation and modeling in SOLIDWORKS and modification of the surface mesh in ANSYS. Further, a way of analyzing the results and some of the outputs of the simulations and analysis has been presented. The CFD simulations were performed on the computational model of an airfoil. The computations were performed for different angle of attacks. It means that the laminar and turbulent flow and several combinations of the angle of attack have been considered.
The research aims to perform a CFD analysis on an aircraft model using FLUENT solver. While performing the simulations, meshing techniques, pre-processing and post processing sections and evaluation of a simulation are being learnt. Coefficient of lift and drag were also recorded. These values were also compared by running different simulations with change of input parameter i.e. angle of attack.

Mragank Pratap Singh, Dr. Mahendra Singh Khidiya, Sahil Soni

Angle of attack; coefficient of drag; coefficient of lift; stall angle of attack.

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Publication Details

Published in : Volume 2 | Issue 3 | May-June - 2016
Date of Publication Print ISSN Online ISSN
2016-06-30 2395-1990 2394-4099
Page(s) Manuscript Number   Publisher
773-776 IJSRSET1623218   Technoscience Academy

Cite This Article

Mragank Pratap Singh, Dr. Mahendra Singh Khidiya, Sahil Soni, "CFD Simulation of an Airfoil at different Angle of Attack", International Journal of Scientific Research in Science, Engineering and Technology(IJSRSET), Print ISSN : 2395-1990, Online ISSN : 2394-4099, Volume 2, Issue 3, pp.773-776, May-June-2016.
URL : http://ijsrset.com/IJSRSET1623218.php

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