The ratio of the K.E. required to be given to | vedclass

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(B) The $K.E.$ required for a satellite to escape from Earth's gravitational field is given by the escape energy: $E_e = \frac{1}{2}mv_e^2 = \frac{1}{

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$2$

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(B) The $K.E.$ required for a satellite to escape from Earth's gravitational field is given by the escape energy: $E_e = \frac{1}{2}mv_e^2 = \frac{1}{2}m(\sqrt{\frac{2GM}{R}})^2 = \frac{GMm}{R}$.The $K.E.$ required for a satellite to move in a circular orbit just above Earth's atmosphere is given by the orbital energy: $E_o = \frac{1}{2}mv_0^2 = \frac{1}{2}m(\sqrt{\frac{GM}{R}})^2 = \frac{GMm}{2R}$.The ratio of these two energies is $\frac{E_e}{E_o} = \frac{GMm/R}{GMm/2R} = 2$.

The ratio of the $K.E.$ required to be given to a satellite to escape Earth's gravitational field to the $K.E.$ required to be given so that the satellite moves in a circular orbit just above Earth's atmosphere is:

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