$A$ satellite of mass $m$ is revolving around the Earth of mass $M$ in an orbit of radius $r$ with constant angular velocity $\omega$. The angular momentum of the satellite is ($G$ = gravitational constant).

  • A
    $m(GMr)$
  • B
    $m(GMr)^{1/2}$
  • C
    $(GMmr)^{1/2}$
  • D
    $\left(\frac{GMr}{m}\right)^{2}$

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