I use one model to compute a result,then gained outlet velocity profile, substitute the profile to another model as its inlet boundary condition.The results show mass flow rate is not consistent with the former model. The question is how to keep mass flow rate unchanged as former model when using velocity profile boundary condition?

thanks in advance.

lcw

[labarc35]

"I use one model to compute a result,then gained outlet velocity profile, substitute the profile to another model as its inlet boundary condition."


How are you doing this substitution? I am trying to do the same thing however I am stuck. I am using COMSOL 4.0. Also Im not sure if I should create a fourier series representation of the outlet velocity profiles for the inlet velocity profile of the new model.

[cactilio86]

If your mass flow is too deviated from the value you had in your first model, then it can mean that your thermal boundary is not the same or you might even have a scaling problem in your mesh. make sure that the thermal profile is also the same and the projected area reported in the outlet of your first model is the same as reported for the inlet of your second model.

Now, if that is ok, it might happen that your mass flow is almost the same, within 5 % more or less. Then you can linearly scale the profile to account for the interpolation error of obtaining and applying the profile to different meshes. You can easily do that with a spreadsheet.

Hope this helps

rgds

Originally Posted by Lcw
;115964

I use one model to compute a result,then gained outlet velocity profile, substitute the profile to another model as its inlet boundary condition.The results show mass flow rate is not consistent with the former model. The question is how to keep mass flow rate unchanged as former model when using velocity profile boundary condition?

thanks in advance.

lcw

Sorry I did not realize this post was SO SO old. Next time I'll check

[hhh]

Dear friends,
In fluent, For analysis of 2D naca0012 airfoil velocity inlet we give vcostheta in x component & vsintheta in y component, v is inlet velocity.

1)here i start analysis of 3D wing, for that i take naca 0012 airfoil & extrude 100mm, in gambit and analysis in fluent i have doubt how to set velocity inlet, here i consider my velocity is 50m/s, then what is xyz component,please let me know.

2)if you consider 3D wing, (vtantheta for z component) is correct or wrong, please let me know.

2) how to find angle of attack for 3D wing? please let me know