If $v_e$ is escape velocity and $v_0$ is orbital velocity of a satellite for an orbit close to the earth's surface,then these are related by:
- A$v_0 = \sqrt{2} v_e$
- B$v_0 = v_e$
- C$v_e = v_0 / 2$
- D$v_e = \sqrt{2} v_0$
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