Determine the drag on a rectangular spacecraft with $1\mathrm{.}3$ m$2$ ram area $($ram area$$ is the

area normal to the spacecraft velocity$)$ and assume Cd$=2$ in a circular orbit around the

earth altitudes of $50,100,150,$ and $200$ km $($use the equations and results from the

previous problems for density and orbit velocity$).$ Use R$/$M $=287($the specific gas constant

for air$).$