\(\frac{1}{2}mv_e^2 = \frac{1}{2}m{\left( {\sqrt {\frac{{2GM}}{R}} } \right)^2} = \frac{{GMm}}{R}\)
\(K.E.\) required for satellite to move in circular orbit
\(\frac{1}{2}mv_0^2 = \frac{1}{2}m{\left( {\sqrt {\frac{{GM}}{R}} } \right)^2} = \frac{{GMm}}{{2R}}\)
The ratio between these two energies \(= 2\)