Aerodynamic performance comparison of airfoils by varying angle of attack using Fluent and Gambit

G. Srinivas, B. P.Madhu Gowda

Research output: Chapter in Book/Report/Conference proceedingConference contribution

4 Citations (Scopus)


Any aircraft wing is the major component which will play vital role in the generation of lift and at different maneuvering moments throughout the flight. So to maintain this good maneuverability the aircraft wing has to undergo deferent deflections called angle of attack such that the high lift and low drag or vice versa can be settled in the flight. Taking this as the motivation the analysis was carried out on the standard wing airfoil comparing with new designed airfoil. Analyze the numerical simulation values like coefficient of lift, coefficient of Drag, Lift, Drag, and Energy parameters with wind tunnel data to predict accuracy for both the airfoils. Through the selected public literature standard airfoil data and designed airfoil data has been chosen, the geometry was created in the GAMBIT and also the meshing by selecting the suitable c-grid and rectangular grid for the better flow analysis in the FLUENT. The mesh file was imported into the FLUENT software there suitable boundary conditions and operating conditions are given for successful flow convergence. Finally analyzing these results are expecting to be best suitable for good aeromechanical features.

Original languageEnglish
Title of host publicationDynamics of Machines and Mechanisms, Industrial Research
PublisherTrans Tech Publications Ltd
Number of pages8
ISBN (Print)9783038351634
Publication statusPublished - 01-01-2014
Event2014 International Mechanical Engineering Congress, IMEC 2014 - Tiruchirappalli, TN, India
Duration: 13-06-201415-06-2014

Publication series

NameApplied Mechanics and Materials
ISSN (Print)1660-9336
ISSN (Electronic)1662-7482


Conference2014 International Mechanical Engineering Congress, IMEC 2014
CityTiruchirappalli, TN

All Science Journal Classification (ASJC) codes

  • Engineering(all)


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