question_answer

The energy required to take a satellite to a height 'h' above Earth surface (radius of Earth \[=6.4\times {{10}^{3}}km\]) 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 (in km) for which \[{{E}_{1}}\] and \[{{E}_{2}}\] are equal, is:

Answer:

3200