A satellite of mass $\frac{M}{2}$ is revolving around earth in a circular orbit at a height of $\frac{R}{3}$ from earth surface. The angular momentum of the satellite is $\mathrm{M} \sqrt{\frac{\mathrm{GMR}}{x}}$. The value of $x$ is
$\_\_\_\_$ , where $M$ and $R$ are the mass and radius of earth, respectively.
( G is the gravitational constant)