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An earth satellite of mass $m$ revolves in a circular orbit at a height $h$ from the surface of the earth. $R$ is the radius of the earth and $g$ is acceleration due to gravity at the surface of the earth. The velocity of the satellite in the orbit is given by
- A$\frac{gR^2}{R + h}$
- B$gR$
- C$\frac{gR}{R + h}$
- D$\sqrt{\frac{gR^2}{R + h}}$
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