Hello all

i am modelling reacting flow in liquid rocket thrust chamber with H2-air one step model.

In the model two inlets for fuel and oxidizer and one outlet pressure conditions.

i tried so many times divergence detected in my problem. 1) how to give the exact pressure boundary conditions at inlet and outlet.

2)what is the solution procedure for compressible species transportation problem.

if anybody knows about this problem please send the information . i am very thankful to u. waiting for ur reply. bye.

One possibility may be in for compressible flows, the inlet conditions are defined as mass-flow rates instead of velocity inlet.

regards kumar

thank u kumar.

but i am getting divergence detected in temperature and floating point error and invalid number. how can i overcome this problem? if any body knows about combustion modelling in fluent pls send suggestions.