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June 20, 2006, 19:16
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Supersonic Cone
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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 |
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