The orbital velocity of an artificial satellite in a circular orbit above the earth's surface at a distance equal to radius of earth is v . For a satellite orbiting at an altitude half of earth's radius, orbital velocity is

Step-by-step solution

The satellite is moving at an attitude above the surface equal to the radius of the earth R . aligned & m v₀^2 2 R =G M m 4 R^2 & v₀= G M 2 R aligned Now if the satellite moves at an attitude equal to R / 2 then, aligned & m v₀^ 2 3 R / 2 =G M m 9 (R / 2)^2 & v₀^ 2 = 2 3 G M R & v₀^ = 2 3 G M R = 2 3 v₀ 2 & = 4 3 v₀= 2 3 v₀ & aligned