The orbital velocity of an satellite in a circular orbit just above the earth's surface is `v`. For a satellite orbiting at an altitude of half of the earth's radius, the orbital velocity is

Options

A. `(3)/(2)v`
B. `sqrt((3)/(2))v`
C. `sqrt((2)/(3))v`
D. `(2)/(3)v`

Answer

c

Explanation

`(V_(C_(2)))/(V_(C_(1)))=sqrt((r_(1))/(r_(2)))=sqrt((R)/(R+(R)/(2)))=sqrt((R)/((3)/(2)R))=sqrt((2)/(3))`
`V_(C_(2))=sqrt((2)/(3))V.`