A) \[\frac{1}{R}\]
B) \[\frac{1}{\sqrt{R}}\]
C) R
D) \[\frac{1}{{{R}^{3/2}}}\]
Correct Answer: A
Solution :
We define kinetic energy of orbiting satellite\[,\]\[KE=\frac{GMm}{2R}\]. Hence \[KE\propto \frac{1}{R}\]You need to login to perform this action.
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