The minimum energy required to launch a satellite of mass $m$ from the surface of earth of mass $M$ and radius $R$ in a circular orbit at an altitude of $2 R$ from the surface of the earth is:
- A$\frac{2 G m M}{3 R}$
- B$\frac{G m M}{2 R}$
- C$\frac{G m M}{3 R}$
- ✓$\frac{5 G m M}{6 R}$
Answer: D.
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