For a satellite orbiting above earth, if the distance above the surface of the earth is increased, its

Linear velocity or orbital velocity is  $v=\sqrt{\frac{\mathrm{GM}}{r}}$

Where r is the distance of the satellite from the centre of the earth.

Therefore v decreases as r is increased. Also $\mathrm{v}=\mathrm{r}\omega$ where $\omega$  is the angular velocity.

Therefore $\omega =\frac{\mathrm{v}}{\mathrm{r}}=\frac{1}{\mathrm{r}}\sqrt{\frac{\mathrm{GM}}{\mathrm{r}}}=\sqrt{\frac{\mathrm{GM}}{{\mathrm{r}}^3}}$

Thus,  $\omega$ decreases with increase in $r$. The time period of the satellite is given by

$\mathrm{T}=2\pi \sqrt{\frac{{\mathrm{r}}^3}{\mathrm{GM}}}$

Thus T increases as r is increased.