Computational Analysis of Fighter Aircraft Wing under Mach Number 0.7 for Small Sweep Angles

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 wor...

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Vydáno v:Applied Mechanics and Materials Ročník 592-594; číslo Dynamics of Machines and Mechanisms, Industrial Research; s. 1020 - 1024
Hlavní autoři: Srinivas, G., Potti, Srinivasa Rao
Médium: Journal Article
Jazyk:angličtina
Vydáno: Zurich Trans Tech Publications Ltd 15.07.2014
Témata:
Angles (geometry)
Computation
Computer simulation
Fighter aircraft
Flight
Guided weapons
Wing design
Wings (aircraft)
CFD
Wing
Transonic
Fighter Aircraft
ISBN:3038351636, 9783038351634
ISSN:1660-9336, 1662-7482, 1662-7482
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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.
AbstractList 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.
Author Potti, Srinivasa Rao
Srinivas, G.
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  email: srinivasapotty@yahoo.co.in
  organization: Manipal University : Dept of Humanities and Management Engg
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Issue Dynamics of Machines and Mechanisms, Industrial Research
Keywords CFD
Wing
Transonic
Fighter Aircraft
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SubjectTerms Angles (geometry)
Computation
Computer simulation
Fighter aircraft
Flight
Guided weapons
Wing design
Wings (aircraft)
Title Computational Analysis of Fighter Aircraft Wing under Mach Number 0.7 for Small Sweep Angles
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