combustion flow simulation in liquid rocket thrust chamber
My objective is to simulate the realistic flow involving combustion of propellant(i.e.liquid fuel and liquid oxidiser)with cooling ,Thus exploring the capabilities of CFD tool and demonstrating its usefulness in supporting the design and optimization process of modern rocket engines.
is there a facility in fluent 6.3.26 for liquid-liquid impingement flame jet or limited to "liquid fuel and gaseous oxidiser" only?
can i get all the performance parameters, temperature,pressure,spatial spray distribution, droplet diameter,thrust obtianable.....
i was going through fluent tutorials can i solve this as"EQUILIBRIUM CHEMISTRY MODEL of NON PREMIXED,NON ADIABATIC,UNSTEADY LAMINAR FLEMELET with SINGLE MIXTURE FRACTION COMBUSTION PROBLEM?
Please someone suggest me with some idea to slove this problem...
thank you for spending ur precious time.
|All times are GMT -4. The time now is 19:59.|