If `v_(e)` is escape velocity and `v_(0)`, is orbital velocity of satellite for orbit close to the earth's surface. Then are related by

Options

A. `v_(0)=sqrt(2)v_(e)`
B. `v_(0)=v_(e)`
C. `v_(e)=sqrt(2v_(0))`
D. `v_(e)=sqrt(2)v_(0)`

Answer

D

Explanation

Orbital velocity of satellite
`v_(0)=sqrt((GM)/R).......(i)`
And escape velocity of satellite
`v_(e)=sqrt((2GM)/R)`
Hence `v_(e)=sqrt(2)v_(0)`