Computational analysis of fighter aircraft wing under Mach number 0.7 for small sweep angles

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

Abstract

Fighter aircraft wings are the leading lift generating components for any aerospace vehicle. The recital of any flying vehicle largely depends on its wing design. Missiles and the fighter aircrafts which are having propulsion system mostly have fins to control and maneuver. In this present paper work an attempt has been made to design a fighter aircraft wing configuration which will be used in some air launched air to surface guided weapons fighter aircraft. The main focus of this paper agreement in determining the Sweep-back effects on fighter aircraft wing under transonic condition at different angles of attack (AoA) from 0 to 5 degrees. For this the fighter aircraft wing performance for various flow conditions and sweep angles are obtained based on the empirical, semi-empirical and CFD simulation results. Hence by studying these computational results would help in the optimizing geometry for better performance, an finest wing design for the air launched air to surface body with conservative wing can be obtained.

Original languageEnglish
Title of host publicationDynamics of Machines and Mechanisms, Industrial Research
PublisherTrans Tech Publications Ltd
Pages1020-1024
Number of pages5
ISBN (Print)9783038351634
DOIs
Publication statusPublished - 2014
Event2014 International Mechanical Engineering Congress, IMEC 2014 - Tiruchirappalli, TN, India
Duration: 13-06-201415-06-2014

Publication series

NameApplied Mechanics and Materials
Volume592-594
ISSN (Print)1660-9336
ISSN (Electronic)1662-7482

Conference

Conference2014 International Mechanical Engineering Congress, IMEC 2014
CountryIndia
CityTiruchirappalli, TN
Period13-06-1415-06-14

All Science Journal Classification (ASJC) codes

  • Engineering(all)

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