  The equations governing motion of the satellite under the effect of
oblateness of Earth and atmospheric drag have been simulated, for a fixed
initial position and three different initial velocities, till satellite
collapses on Earth. Simulation of motion of artificial Earth satellite subject
to the combined effects of oblate Earth and atmospheric drag is presented. The
atmospheric model considered here takes in to account of exponential variation
of the density with initial distance of Satellite from Earth's surface, scale
height and radial distance. The minimum and maximum values of orbital elements
and their variation over a time for different initial velocities have been
reported.
