An artificial satellite moving in circular orbit around the earth has a total (kinetic + potential) energy E0. Its potential energy and kinetic energy respectively are

2E0 and –2E0 -2E0 and 3E0 2E0 and –E0 -2E0 and –E0

2E0 and –E0

K.E. = $\frac{GMm}{2 r}=-E_0$, and  P.E. = $-\frac{GMm}{r}=2 E_0$ ⇒ T.E. = K.E. + P.E. = $-\frac{GMm}{2 r}=E_0$