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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