For a satellite moving in an orbit around the earth, the ratio of kinetic energy to potential energy is -

\(\frac{1}{\sqrt{2}}\) 2 \(\sqrt{2}\) \(\frac{1}{2}\)

\(\frac{1}{2}\)

Potential Energy : U = \(-\frac{GMm}{r}\) Kinetic Energy : K = \(\frac{1}{2} mv^2\) ; velocity : v = \(\sqrt{\frac{GM}{r}}\) ⇒ Kinetic Energy : K = \(\frac{1}{2}\frac{GMm}{r}\) ∴ Ratio : \(\frac{K}{U} = \frac{1}{2}\)