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 :

v_{o} = v_{e}

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v_{e} = \sqrt{2 v_{o}}

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v_{e} = \sqrt{2} v_{o}

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v_{o} = \sqrt{2} v_{e}

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Solution

The correct option is C $v_{e} = \sqrt{2} v_{o}$
$v_{e s c a p e} = \sqrt{\frac{2 G M}{R}}$
$v_{o r b i t a l} = \sqrt{\frac{G M}{R}}$
$v_{e s c a p e} = \sqrt{2} v_{o}$

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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 :

The correct option is C $v_{e} = \sqrt{2} v_{o}$
$v_{e s c a p e} = \sqrt{\frac{2 G M}{R}}$
$v_{o r b i t a l} = \sqrt{\frac{G M}{R}}$
$v_{e s c a p e} = \sqrt{2} v_{o}$