Hi,
I am trying to learn how to calculation the lift and drag coefficient of an airfoil running a time-dependent study.
Below are the boundary conditions.
Re ~2000
Inlet- Inlet U*step1(t[1/s])
Top and bottom- Slip
Outlet- Pressure no viscous stress
My problems the Lift coefficient (CL) values seems like it keep going down as time goes.
Re~2000 but would like to increase it to 10^7.
I am not sure what's wrong with my setup?
I set it up based on the model in the Library (Flow past a cylinder). File is too large cannot be attached so screenshots are attached instead.
Thank you very much for your time!
Ting
I am trying to learn how to calculation the lift and drag coefficient of an airfoil running a time-dependent study.
Below are the boundary conditions.
Re ~2000
Inlet- Inlet U*step1(t[1/s])
Top and bottom- Slip
Outlet- Pressure no viscous stress
My problems the Lift coefficient (CL) values seems like it keep going down as time goes.
Re~2000 but would like to increase it to 10^7.
I am not sure what's wrong with my setup?
I set it up based on the model in the Library (Flow past a cylinder). File is too large cannot be attached so screenshots are attached instead.
Thank you very much for your time!
Ting