The energy required to take a satellite to a height ' $h$ ' above Earth surface (radius of Earth $=6.4 \times 10^3 \mathrm{~km}$ ) is $E_1$ and kinetic energy required for the satellite to be in a circular orbit at this height is $E_2$. The value of $h$ for which $E_1$ and $E_2$ are equal, is
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