|November 18, 2013, 06:37||
not getting Mach no 1 at throat
Join Date: Nov 2013
Posts: 1Rep Power: 0
i am using fluent for supersonic nozzle design..
but some how i am get mach number is one at throat section,
i used k-e model,segregated solver,boundary condition is given mass flow rate inlet and pressure outlet,in result i get constant density throughout nozzle.please help me.my outlet pressure is 0.80 bar and mass flow rate inlet is 11.11 kg/s.
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