A) \[\sqrt{G{{M}_{e}}{{m}_{s}}R}\]
B) \[\sqrt{G{{M}_{e}}{{m}_{s}}^{2}R}\]
C) \[\frac{\sqrt{G{{M}_{e}}{{m}_{s}}^{2}}}{R}\]
D) \[\frac{\sqrt{G{{M}_{e}}{{m}_{s}}}}{R}\]
Correct Answer: B
Solution :
Angular momentum of a satellite \[=\sqrt{G{{M}_{e}}M\,_{s}^{2}R}\]
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