The ratio of the kinetic energy required to be given to the satellite to escape earth’s gravitational field to the kinetic energy required to be given so that the satellite moves in circular orbit just above earth’s atmosphere is

Two

$\frac{(\mathrm{KE})_{\text {escape }}=\frac{1}{2} \mathrm{~m} \mathrm{v}_{\mathrm{e}}^2}{(\mathrm{KE})_{\text {orbit }}=\frac{1}{2} \mathrm{~m} \mathrm{v}_0^2}=\frac{\mathrm{v}_{\mathrm{e}}^2}{\mathrm{v}_0^2}=\frac{\frac{2 \mathrm{GM}}{\mathrm{R}}}{\frac{\mathrm{GM}}{\mathrm{R}}}=2$