If \[{{v}_{e}}\] and \[{{v}_{o}}\] represent the escape velocity and orbital velocity of a satellite corresponding to a circular orbit of radius R, then [CPMT 1982; MP PMT 1997; KCET (Engg./Med.) 1999; AIIMS 2002]

• A.             \[{{v}_{e}}={{v}_{o}}\]
• B.             \[\sqrt{2}{{v}_{o}}={{v}_{e}}\]
• C.             \[{{v}_{e}}={{v}_{0}}/\sqrt{2}\]
• D.             \[{{v}_{e}}\] and \[{{v}_{o}}\] are not related