Methods of drag reduction by modifying landing gear system in fighter aircraft
Abstract
In the present paper, the effect of the change of position and change of dimension (modification) of the landing gear on the drag reduction of the fighter aircraft have been studied. Modeling of the landing gear of model 1 to model 4, have been done using Catia V5 and numerical simulation have performed using CFD to evaluate the coefficient of drag, velocity, turbulence intensity and static pressure. The modification of landing gear results in a reduction of the drag coefficient. The drag coefficient for model 1 was found 1.37. Whereas, for model 4 the drag coefficient was reduced to 0.46. The maximum drag reduction was achieved for model 4 is about 66%. The drag reduction of fighter aircraft would directly affect the fuel consumption, rang, and endurance of the fighter aircraft.
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