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July 18, 2012, 10:02 |
nozzle plume_convergence problem
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New Member
masood
Join Date: May 2012
Posts: 18
Rep Power: 13 |
hi .
i have to find nozzle plume of a rocket in 3d simulation . im not sure to use presssure farfield or pressure outlet for my computation domain and why ? im using rng ke - density based - ideal gas . after about 100 iteration my solution diverges . i have checked boundary condition and viscous models many times but i could not find the problems . mostly the error is floating point number error . the inlet condition is 2800 kelvin and 140 bar .do you think its a supersonic flow ? and shock happens ? i have attached a simplied picture of the model (the nozzle is cutted by an angle) . do you have any idea what is wrong ?? thanks in advance . |
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