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
- A${v_e} = {v_o}$
- B$\sqrt{2} {v_o} = {v_e}$
- C${v_e} = \frac{{v_o}}{\sqrt{2}}$
- D${v_e}$ and ${v_o}$ are not related
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