AIR intake for fighter aircraft
 

Hi everyone, I am simulating flow through an air intake duct with pressure ratio 0.85, i specified bc's as pressure farfield for flow entering ( 0.1 MACH and pr = 101325) and outlet (-14500pa ) to set back pressure, but i am getting error mesg that flow as been reversed on outlet faces, later i reduced Courant number and tried but residuals are not converging ... so anybody please rectify this problem.

computational modeling of intake
 

hi
Due to the complex physics of the flow separation intake, it seems that there is a need for more computational space. Add the duct end to the computational field of intake.