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Flow Analysis over an F-16 Aircraft Using Computational Fluid Dynamics

By Manish Sharma, T. Ratna Reddy and Ch. Indira Priyadarsini


Abstract — In the current era of globalization every prosperous nation in this world wishes to develop a fast moving aircraft with a high lift coefficient and low drag coefficient, which helps them to enhance their military force and strengthens its civilization’s foundation. The purpose of this study is to examine the viscous, incompressible and steady-state flow over the F-16 aircraft using computer modelling techniques and to compare the modelled results with the experimental results done with the help of wind tunnel. This paper outlines the development of a computational model of the F-16 model in modelling software and then the creation of a finite computational domain, segmentation of this domain into discrete intervals, application of the boundary condition such as Mach number or velocity and then obtaining the plots and results for coefficient of pressure, lift coefficient, drag coefficient, etc. The aircraft being a military aircraft travels at speed of Mach 2, which is around 1,500 mph at an altitude of 50,000 ft. This paper will give the future generation to think in a manner to develop the aerospace field and the CFD field too. The pilot has excellent flight control of the F-16 through its "fly-by-wire " system. Electrical wires relay commands, replacing the usual cables and linkage controls. For easy and accurate control of the aircraft during high G-force combat manoeuvres, a side stick controller is used instead of the conventional centre-mounted stick. Hand pressure on the side stick controller sends electrical signals to actuators of flight control surfaces such as ailerons and rudder

Topics: Drag Coefficient (C D, F-16 Aircraft
Year: 2014
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