The semi-major axis of the orbit of satellite

Now semi–major axis a = $\frac{-GMm}{2 E}=-\frac{6.67 \times 10^{-11} \times 5.97 \times 10^{24} \times 5000}{2 \times\left(-1.5 \times 10^{10}\right)}$

= 6.6 × 10⁷ m