1. The problem statement, all variables and given/known data Initial mass of the rocket is M = 30 x 10^3 kg, while its initial acceleration a = 3g. The rocket has four nozzles of diameter D = 20 cm each. Burning fuel leaves the nozzle with velocity v = 2.0 km/s having temperature T = 600◦C. Assuming fuel is burned completely and the exhaust gas is carbon dioxide CO2, determine its pressure P at the nozzle exit. Neglect air resistance. 2. Relevant equations What is the best way to approach this problem? Most of the time I can get the problem started because I know what I'm dealing with in terms of what chapter the topic came from. I'm thinking I'm going to have to do something with the ideal gas law but I was told the problem would not have to worry about degree of freedom. I just need a booster so I can begin to work something out. (Thanks again to the last guys who helped me) 3. The attempt at a solution Unfortunately, this is one of the few times I had nothing to start with. All I figured out thus far is that I will need to know that CO2 is 44g/mol.