model ignite transient process
Hi,everyone I meet problems when modeling the ignite transient process for solid rocket motor. As we know, befor burning the propellent surface for solid rocket motor is regarded as wall boundary,but after it is burned,exhaust gas release form the surface so it must be regarded as mass inflow boundary. Because when and where the propellent suface is burned is not known previously, how could I set such a boundary? I need you help urgently, Thanks a lot!
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