Supersonic Cone
 

Hey everybody

I am modelling a supersonic cone, i did it as 2d axisymmetric, my boundary conditions are pressure_far_field at the front, behind and above the cone. i did 3 differnt "pressure far field" boundary conditions;at the front i entered Mach=2.5 gauge pressure=506625, Temp=300k. i entered the other pressure far fields as M=0.04, and gauge pressure=0 i used coupled solver i got float point error i set operating pressure to 0 i also tried Mach=2.5 gauge pressure=0, Temp=300k. but i got the same error i also want to know when do i set the axial flow component to 1 and when do i set it to -1