Calculate the speed required for a satellite moving in a circular orbit 550.0 km above the surface of the Earth. (mEarth = 5.98 × 1024 kg , rEarth = 6.38 × 106 m)

Answer 1

m v^2/R = m g there = G m M / R ^ 2
m cancels of course
so
v^2 = G M/R
R = 6.38*10^6 + 0.550 *10^6
M = 5.98*10^24
G= 6.67 *10^-11