Some future update mod ideas/wishlist

@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.
View attachment 14792

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.
View attachment 14793
@Altaïr Do you think it is feasible for the engine's exhaust to have such a low pressure? I am kinda worried of the values I am getting there.
 

Altaïr

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@Altaïr Do you think it is feasible for the engine's exhaust to have such a low pressure? I am kinda worried of the values I am getting there.
Oh sorry, I forgot that. I was working on my Grand Tour attempt last week and I also had to answer a few questions (resonant orbits...).
I didn't check the calculations but it seems very low indeed. I'll give this a try, but it's been long I didn't practice fluid mechanics, so it won't be easy for me.
 
Oh sorry, I forgot that. I was working on my Grand Tour attempt last week and I also had to answer a few questions (resonant orbits...).
I didn't check the calculations but it seems very low indeed. I'll give this a try, but it's been long I didn't practice fluid mechanics, so it won't be easy for me.
I just used NASA's equations, and assumed the specific heat ratio to be the typical 1.2.