[wolfy_01]

Actually I have asked this question before but I dont understand the logic. If you can shed some light would be grateful.

I have been given pressure ratio and efficiency which are the design requirements of a propulsive device. In order to model an aero-propulsive device, my professor has said to give pressure outlet BC with targeted massflow at the inlet and stagnation inlet BC at the outlet.

So, StarCCM+ is calculating the total pressure and total temperature at the outlet and static temperature and static pressure at inlet with certain massflow. To my understanding, it is an actuator disk approach to model the propulsive device.

Is this a normal way to approach a turbomachinery problem? What is the logic behind giving such a boundary condition? Could anyone please explain?

Also any books that I can refer for better understanding of the subject as I am new in CFD and aerospace

Thanks in immense,
With Best Regards,
Swaroop

[fluid23]

That does indeed seem backwards. Why would you have a stagnation outlet? That makes no physical sense to me. Perhaps someone else has a better answer.