Question

If $v_0$ be the orbital velocity of a satellite in a circular orbit close to the earth's surface and $v_e$ is the escape velocity from the earth, then relation between the two is

• A. $v_e=2v_0$
• B. $v_e=\sqrt{3}{v}_0$
• C. $v_e=v_0\sqrt{2}$
• D. $v_0=v_e$

Answer 1

The correct option is C $v_e=v_0\sqrt{2}$

$Answer:-$ C

For a spherically symmetric massive body such as a star or planet, the escape velocity for that body, at a given distance is calculated by the formula:

For orbital velocity of a satellite in a circular orbit close to the earth's surface:-

$v_0=\sqrt{\frac{Gm}{R}}$

Hence, $v_e=\sqrt{2}{v}_0$