If v_e is escape velocity and v_o is orbital velocity of a satellite for orbit close to the earth's surface, then these are related by :

• A

  ${\mathrm{v}}_{\mathrm{e}}=\sqrt{2{\mathrm{v}}_0}$

• B

  ${\mathrm{v}}_{\mathrm{e}}=\sqrt{2}{\mathrm{v}}_0$

• C

  ${\mathrm{v}}_0=\sqrt{2}{\mathrm{v}}_{\mathrm{e}}$

• D

  v_o = v_e