Assume that the rocket nozzle of the previous problem is designed to develop a thrust of 1MN at an altitude of 10 km. Determine the thrust developed by the nozzle at 20 km, for the same stagnation conditions in the thrust chamber. Take the ambient pressure and temperature at 10 km to be 26.15 kPa and 223 K. Do you expect to see a normal shock in the nozzle divergent portion during sea-level operation?