The orbital velocity of an artificial 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

Question

The orbital velocity of an artificial 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 (A) (3/2)v (B) √(3/2)v (C) √(2/3)v (D) (2/3)v

Tardigrade Admin · Accepted Answer

We know that v0=√(G M/R) for a satellite at at altitude (R/2) , v1=√(G M/(R + (R)2)) therefore (v1/v)=√(2/3)

Q. The orbital velocity of an artificial 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

$\frac{3}{2} v$

$\frac{3}{2} v$

$\frac{2}{3} v$

$\frac{2}{3} v$

We know that $v_{0} = \frac{GM}{R}$ for a satellite at at altitude $\frac{R}{2}$ ,
$v_{1} = \frac{GM}{( R + \frac{R}{2} )}$
therefore $\frac{v _{1}}{v} = \frac{2}{3}$

Q. The orbital velocity of an artificial 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

23​v

23​​v

32​​v

32​v

We know that v0​=RGM​​ for a satellite at at altitude 2R​ , v1​=(R+2R​)GM​​ therefore vv1​​=32​​

Q. The orbital velocity of an artificial 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

$\frac{3}{2} v$

$\frac{3}{2} v$

$\frac{2}{3} v$

$\frac{2}{3} v$

We know that $v_{0} = \frac{GM}{R}$ for a satellite at at altitude $\frac{R}{2}$ ,
$v_{1} = \frac{GM}{( R + \frac{R}{2} )}$
therefore $\frac{v _{1}}{v} = \frac{2}{3}$