NASA ROTOR 67 modelling
I am trying to model the same rotor with fluent. my domain is extended enough ( i think). i have tested almost everything but i can not obtain the correct pressure ratio for the design mass flow rate. i am using standard k-w turbulance model with 1% of turbulent intensity and 0.0001 turbulant length scale. I have tested both pressre based solver and density based solver. i have tested also diffrent combinations for inlet and outlet boundary condition. for inlet mass flow inlet or pressure inlet and at outlet pressre outlet with/without targeting the massflow rate and radial equilburim activated.
i will be thankful to recive your recomandations.
(I can post also my case if you want to check)
acctually i am working with the grid that is on stansford university website. but at the moment i have some douts about the soliution procdure (as its my first case on rotors) .
i have seen that some guys are usingnot a extended geomtry in a way that inlet and outlet are placed in a position that experimental values of pressure and temperure and etc are avilable. but in my case geomtry is extended ( suppuse that it is enough). then i have just the pressure ratio and mass flow rate and temperate and pressure at inlet and some how the tempretaure at outlet.
number of blade=22
at the moment the temperature is not convergaing with density based solver ( and i have the warning related to "Temperature limited" )
but with pressure based solver everything is converging
the problem is that for both cases the pressure ratio is small maximum 1.5
and with mass flow is correct ( as i am using target mass flow rate)
i dont know exactly but i thinck there should be sth beyond grid (in fact my spanwise Mach number distrubition is not even similar :( to the correct results
with pressure based solver i was able to obtain the correct pressure ratio and massflow rate. but still the distribution of Mach number is strange spesially near the out let.
Were you able to get this to work?
I havent been successful so far, i could use some help
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