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...

Full description

Saved in:
Bibliographic Details
Published in:Applied Mechanics and Materials Vol. 592-594; no. Dynamics of Machines and Mechanisms, Industrial Research; pp. 1020 - 1024
Main Authors: Srinivas, G., Potti, Srinivasa Rao
Format: Journal Article
Language:English
Published: Zurich Trans Tech Publications Ltd 15.07.2014
Subjects:
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
Online Access:Get full text
Tags: Add Tag
No Tags, Be the first to tag this record!
Description
Summary: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.
Bibliography:Selected, peer reviewed papers from the 2014 International Mechanical Engineering Congress (IMEC 2014), June 13-15, 2014, Tamil Nadu, India
ObjectType-Article-1
SourceType-Scholarly Journals-1
ObjectType-Feature-2
content type line 14
content type line 23
ISBN:3038351636
9783038351634
ISSN:1660-9336
1662-7482
1662-7482
DOI:10.4028/www.scientific.net/AMM.592-594.1020