[mahdidelfan]

hi
my numerical simulation by ansys fluent15 .but i can not get a good simulation.i can not get Static pressure distributions along the central symmetrical line of the scramjet isolator with a constant cross sectional area for back pressures 100 kp. my domain is a quarter of the original geometry.in my domain Using tow symmetry boundary conditions and tow wall boundary condition

mesh is 69*69*261 in (Depth,Height and length, respectively)

simulation Boundary conditions and solution setup is:
solver=pressure-based
Steady State
model: standard k- epsilon

energy=on

near wall treatment:standard wall function

material:air ideal gas


boundary condition:
inlet pressure inlet

Total Pressure = 196000 [Pa


Static Pressure = 25050 [Pa


thermal=300 k


: outlet

pressure outlet =100 [kPa
thermal=300 k
wall
Adiabatic
No Slip Wall


solution method=

pressure-velocity copling

sheme=coupled

spatial discrezation=secund order upwind

and enable pseudo transint


solution control

pseudo transint explicet relaxtion factor=

pressure=0.5

momentume=0.5

density=0.5

energy=0.75

turbulent kinitic energy and dissipation rate=0.9


solution initialization=hybrid

my rsedual not converged




Please see the attached images.
Please Guidance me.
Thank you