A) 41%
B) 61%
C) 81%
D) 98%
Correct Answer: A
Solution :
[a] Orbital velocity for close to earth orbits \[=\sqrt{gR}\]. Escape velocity required \[=\sqrt{2gR}\]. % Increase required \[=\frac{{{v}_{e}}-{{v}_{0}}}{{{v}_{0}}}\times 100\] \[=\frac{\sqrt{gR}\left( \sqrt{2}-1 \right)}{\sqrt{gR}}\times 100=41%\]
You need to login to perform this action.
You will be redirected in
3 sec
