@Altaïr Alright so here is another update, this is the basic graph template I plan to use for the report. The dotted line is the rate of pressure drop over 50 kilometers of altitude, its been made linear for easier viewing.
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I also attempted to figure out the exhaust pressure manually, my numbers for exhaust pressure for seal level pressure is 283 pascal and for vacuum pressure is 31 pascal. It feels weird though, could you help me double check the calculations? By the way I assumed the specific heat ratio of the rocket engine to be the typical 1.2, and the other engineers I consulted told me that the engines running on LOX/LH2 can have a chamber temperature of 3400 K, throat temperature of 3050 K and exhaust temperature of 685 K.
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