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Urgent Help/3D Wing lift and drag
Posted 26 ott 2021, 20:59 GMT-4 Structural & Acoustics, Fluid & Heat, Computational Fluid Dynamics (CFD) 2 Replies
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Hi, I hope everyone is doing good. I am solving 3D wing model and I am calculating lift and drag using the formulae. I am new to COMSOL. I am using following equations;
Lift= 2spf.T_stressy/(0.077257rho_infU_inf^2) ny(ny>0)+nz*(nz>0)
Drag = -2spf.T_stressz/(0.077257rho_inf*U_inf^2)
where my flow direction is -y direction and z axis is perpendicular direction (lift direction).
But I am not obtaining reasonable results. I hope your insights can help me accordingly. I have attaching some pictures of the sim file as well.
Thank you.
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Hello Musavir,
Can you clarify what results do not appear reasonable to you? Is it the flow computed, or the integrals computed, or something else...?
I strongly recommend you upload your .mph file (stripped of the mesh and solution to reduce file size) to obtain more meaningful feedback from Discussion Forum users. Without it, trying to help you is akin to joining a game of blindfold chess halfway through the game...
Best,
Jeff
-------------------Jeff Hiller
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Hi Jeff, Thank you for your reply and precious time. I am hereby attaching the solution file. I have cleaned the mesh and solution. I am not getting good results as I compared with already existing results. Thank you.
Regards,