$A$ satellite of mass $m$ is in a circular orbit of radius $2R_E$ around the Earth. The energy required to transfer it to a circular orbit of radius $4R_E$ is (where $M_E$ and $R_E$ are the mass and radius of the Earth,respectively).
- A$\frac{GM_Em}{2R_E}$
- B$\frac{GM_Em}{4R_E}$
- C$\frac{GM_Em}{8R_E}$
- D$\frac{GM_Em}{16R_E}$
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