Boundary Condition Values for NASA Rotor 37
 

Hello guys, I am new to turbomachinery simulation. I am going to perform simulation of Nasa Rotor 37 in Ansys CFX using Turbo Mode. (not stage just rotor).

As per literature i should use Total Pressure inlet and Static Pressure outlet BCs. My questions :

1. What should be the value of Total Inlet Pressure?
2. What should be the value of Reference Pressure ? (1 atm? )

As per the case , we have to change the Static Pressure outlet values from 99215 Pa to 124027 Pa. In order to see the changes in Mass flow rate right?

Kindly guide me and sorry for asking such basic questions.

Thanks in advance

288.15k and 1 atm. Altering the back pressure is to simulate different operating conditions.

Thanks for your reply. and what should be the value for Reference Pressure ? Should i put it as 1 atm or 0 atm ?

Both are OK. Be careful that after setting the ref, other pressure values in software are equal to the real values minus by it.