If an earth satellite is put in orbit at a height where resistance due to the atomosphere cannot be neglected, how will the motion of a satellite be affected ?

Explanation

For a satellite, moving in a circular orbit of radius r orbital velocity `V_0=sqrt((GM)/r)therefore Its K.E.=1/2mV_0^2=^1//_2m(GM)/r=^1//_2(GMm)/(2.r)and it's ` PE(GMm)/rxxr/(GMm)=^1//_2`