[BEEL]

Hello all,
I am a student trying to simulate combustion of hybrid rocket chamber.
I have no experience in this field, so I practice with Dr. Bellomo et al 's work.
(http://www.enu.kz/repository/2010/AIAA-2010-7033.pdf)

Most of the settings follows that in the paper except using Fluent and axisymmetric grid. but it shows different results to the paper and the trend is complete wrong compared to the experimental data.

the settings is
1. mass flow rate N2O(g) and mass flow rate C2H4(g)
2. ideal gas, Cp depends on Temperature, viscosity=sutherland's law for air
3. eddy dissipation method ,A=4, B=0.5


my problems is:
1. I try both pressure based solver and density based solver, they agree on the same result for the coldflow , but very different if EDM is added. Reactions using pressure based solver are much faster than the density based one. is something wrong?

2. compared my result(density based solver, with diaphragm) to the paper, N2O and C2H4 are mixing badly which forms clear boundary between the two, and the n2o is left about 30% unreacted at the outlet . The diffusion flame is thinner, farther to the propellant wall. it seems that the reattachment length is longer.


I have tried everything I can think of and been quite frustrating.

THANKS FOR ANY ADVICE