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(B) The orbital velocity $v_0$ of a satellite orbiting at a height $h$ above the Earth's surface is given by $v_0 = \sqrt{\frac{GM}{R+h}}$.For a satel

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The radius of the earth only

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(B) The orbital velocity $v_0$ of a satellite orbiting at a height $h$ above the Earth's surface is given by $v_0 = \sqrt{\frac{GM}{R+h}}$.For a satellite orbiting very close to the Earth's surface,the height $h$ is negligible compared to the radius of the Earth $R$ (i.e.,$h \approx 0$).Thus,the formula becomes $v_0 = \sqrt{\frac{GM}{R}}$.Since $g = \frac{GM}{R^2}$,we can write $GM = gR^2$.Substituting this into the velocity formula: $v_0 = \sqrt{\frac{gR^2}{R}} = \sqrt{gR}$.Therefore,the orbital velocity of a satellite close to the Earth's surface depends on the acceleration due to gravity $g$ and the radius of the Earth $R$.

If a satellite is orbiting the earth very close to its surface,then the orbital velocity mainly depends on

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