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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
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Verified Answer
The correct answer is:
$v_e=\sqrt{2 v_o}$
Orbital velocity of satellite
$$
v_o=\sqrt{\frac{G M}{R}}
$$...(i)
and escape velocity of satellite
$$
v_e=\sqrt{\frac{2 G M}{R}}
$$...(ii)
Hence, $\quad v_e=\sqrt{2} v_o$
$$
v_o=\sqrt{\frac{G M}{R}}
$$...(i)
and escape velocity of satellite
$$
v_e=\sqrt{\frac{2 G M}{R}}
$$...(ii)
Hence, $\quad v_e=\sqrt{2} v_o$
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