The orbital velocity of an artifical satellite in a cirular orbit above the earth's surface at a distance equal to radiu of earth is v. For a satellite orbiting at an altitude half of earth's radius, 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

Since, orbital velocity `v=sqrt((GM)/(r))or v prop (1)/(sqrt(r))`
`(v_(2))/(v_(1))=sqrt((r_(1))/(r_(2)))`
`:. v_(2)=sqrt((r_(1))/(r_(2))).v=sqrt((R)/(R+(R)/(2))).v=sqrt((2)/(3))v`.