Given data
*The given mass of the Earth is M_e = 6.0 × 10^24 kg
*The distance above the surface of the Earth is r = 1683049 m
The formula for the speed of the satellite must be traveling so that it shall remain in a circular orbit is given as
[tex]v=\sqrt[]{\frac{GM_e}{r}}[/tex]Substitute the known values in the above expression as
[tex]\begin{gathered} v=\sqrt[]{\frac{(6.67\times10^{-11})(6.0\times10^{24})}{(1683049)}} \\ =1.54\times10^4\text{ m/s} \end{gathered}[/tex]Hence, the speed of the satellite must be traveling so that it shall remain in a circular orbit is v = 1.54 × 10^4 m/s
