Chapter 5.3, Problem 14E

(a)

To determine

To prove: That the approximate value of the constant $c$ of integration is $c=-gR+\frac{1}{2}{\nu }_0^2$.

(b)

To determine

To prove: That the escape velocity of the rocket is ${\nu }_0=\sqrt{2gR}$.

(c)

To determine

To prove: That the escape velocity from the earth is approximately ${\nu }_0=25000\text{ mi/h}$.

(d)

To determine

To evaluate: The escape velocity from the Moon.