1.1 Revisit. Rework Problem 1.1, but now using a thermodynamic analysis assuming complete combustion. Determine the vacuum specific impulse Isp,vac of an oxygen-hydrogen rocket engine with an oxidizer-to- fuel mixture ratio by weight of 4.0:1. Calculate adiabatic flame temperature assuming complete combustion with a chamber pressure of 68 atm through a convergent-divergent nozzle expanded to vacuum. Report the product flame temperature and molecular weight. Calculate the specific impulse. Compare your values to those from Problem 1.1. Discuss and assess your results with consideration of the chemical composition of the exhaust products. Assume hydrogen and oxygen at 298.15K. Assume adiabatic and isentropic flow through the nozzle with an expansion area ratio = 50:1. Note, you will need thermodynamic enthalpy tables for H2, O2 and H2O as a function of temperature.