If \( v_{e} \) and \( v_{0} \) represent the escape velocity and orbital velocity of a satellite...
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If \( v_{e} \) and \( v_{0} \) represent the escape velocity and orbital velocity of a satellite corresponding to a circular orbit of radius \( R \), then \( \quad \) [CPMT 1982; MP PMT 1997;
KCET (Engg./Med.) 1999; AIIMS 2002; RPMT 2006;
Odisha JEE 2011; Similar CBSE PMT (Mains) 2012]
(a) \( v_{e}=v_{o} \)
(b) \( \sqrt{2} v_{o}=v_{e} \)
(c) \( v_{e}=v_{o} / \sqrt{2} \)
(d) \( v_{e} \) and \( v_{o} \) are not related
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