Multiphase setup for Rocket nozzle simulation
 

I am an undergrad student. I am doing a fun project to simulate the rocket nozzle. I understand that to properly simulate the system, I have to use the multiphase model. First phase would be liquid propellant(which is RP-1 in my case) and second phase would be exhaust gases. I am very new to this concept so can someone please help me with it? I have searched lots of youtube videos and articles but couldn't find quite what I needed.

Thank you in advance for reading all this!

Objective
 

What is the objective of the simulation? If it is flow of products through the nozzle for studying the nozzle, I'd recommend not to go into multiphase since you are new to this and heterogeneous reactions could be difficult. If you want to study combustion of liquid propellant and oxidizer, then you have to look at the conditions at which reactions occur. If it is near critical conditions, which is the case for most cryogenic systems, then it is not multiphase but real-gas modeling that you need.

Thank you so much. I only want to simulate flow of the products through the nozzle. So, I guess I'll just simulate the flow. Just to be sure can you check the boundary conditions?

Pressure inlet: 3-5 bar pressure, 1200K temp
Pressure outlet: 0.7-1 bar pressure, 260-300K temp

I haven't finalized boundary condition yet as I have to calculate theoretically but it will be in this range mostly... Are they right? I have seen papers with inlet pressure vary from 2 bar to 200 bar so I am confused about it.

Thank you in advance.:)

Boundary Conditions
 

Yes, the boundary conditions are alright. The values depend upon the conditions you want to simulate for.

Thank you so much