• # question_answer The orbital velocity of an artificial satellite in a circular orbit just above earth's surface is ${{v}_{0}}$.For a satellite orbiting in a circular orbit at an altitude of half of earth's radius is A)  $\sqrt{\frac{3}{2}}{{v}_{0}}$                   B)  $\sqrt{\frac{2}{3}}\,{{v}_{0}}$ C)  $\sqrt{\frac{5}{3}}\,{{v}_{0}}$                 D)  None of these

Orbital velocity at an altitude eh from the earth surface $=\sqrt{\frac{{{g}_{0}}{{R}^{2}}}{R+h}},$ where R is radius of earth. If          $h=0,\,\,{{v}_{0}}=\sqrt{\frac{{{g}_{0}}{{R}^{2}}}{R}}=\sqrt{{{g}_{0}}R}$ If $h=\frac{R}{2},\,\,v=\sqrt{\frac{{{g}_{0}}{{R}^{2}}}{R+\frac{R}{2}}}=\sqrt{\frac{2{{g}_{0}}R}{3}}=\sqrt{\frac{2}{3}}{{v}_{0}}$