The orbital velocity of an artificial satellite in a circular orbit very close to earth is $v$. The velocity of a geo-stationary satellite orbiting in circular orbit at an altitude of $3R$ from earth's surface will be
The orbital velocity of an artificial satellite in a circular orbit very close to earth is $v$. The velocity of a geo-stationary satellite orbiting in circular orbit at an altitude of $3R$ from earth's surface will be
- A
$\frac{v}{{\sqrt 7 }}$
- B
$\frac{v}{{\sqrt 6 }}$
- C
$\frac{v}{2}$
- D
$\frac{v}{{\sqrt 2 }}$
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