How to find lift coefficient by fluent?
Hi everybody,
I used fluent to model flow around NACA 0015. I got cl & Cd for the same flow and airfoil from Xfoil and want to compare Xfoil results with fluent results. I want to find Cl and Cd by fluent and my problem is the numbers which I have to enter for X,Y,Z of force vector. do you know what should I put in there and how many iterations should I have at least to get acceptable answer for Cl and Cd? Thank you in advance 
enter 1 0 0 for Force Projection on xaxis
enter 0 1 0 for Force Projection on yaxis enter 0 0 1 for Force Projection on zaxis Now choose the right force you want to observe, and enable the plot option in monitor/force Fluent will plot the accorded Coeff while iterating. Your solution will be full converged if the the plotted coefficient remains constant while iterating. You also have to set the right reference values for getting the right Coefficient 
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before iterations, set "monitorslift" and define the lift vector (ex: y=1)
and select your airfoil (must be a wall) for which the lift will be monitored. also dont forget to set correct ref. values. than begin iteration and it will show you "cl" in each step by default. 
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Area: What value should i use?? The edge length of the airfoil multiply by the depth??? Depth: is this the length of the wing?? 
Check tutorial 3: Modelling external compressible Flow.
The references values you give are independant from your solution. Compute your model, and then you can apply your refences values. Even if you gave wrong Ref. Values, you can correct them without reiterating. They are just factors. Important are pressure and viscous forces computed during iterations 
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I have the same problem and your answer indeed helped me a lot. I have monitored the Cl and Cd and while iterating I found out that my coefficients are not constant in the plot what I am supposed to do in this situation. Please explain in details I am a beginner.
Check pictures attached. R.I.P for your dear friend Herve. Thanks 
Hi max...i figure it out that if i change the depth on reference values i get differents cl y cd results..why is that if the equation is: Cl=F/(0.5*density*velocity*velocity*Area)..
Another question what if the angle of attack is different than zero, which velocity value on farfield should be taken to calculate the lift coefficient??? 
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*I would say you can take the cosine of your angle as factor. But since the angles are small, it won't affect your coeff (needs to be confirmed/invalidate from aero experts). Check tutorial 3 and compare velocity value given in Ref. with Mach Number 
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Is my solution converged, and how to compare 1st order with 2nd I am running now in 2nd order (pressure and momentum). I see no difference really is the difference from the drag and lift forces or the plot of the iterations to drag. How to do a GIS, I probably done it already? R.I.P to your friend again :( 
you need also to check your residuals (plot/residuals...)
If all the residuals fall down, let iterate and check if your monitoring still stay constant. Regarding your comparison between first and second order: write your force monitoring on a file (one file for 1st order, and one for second). Write also case and data before switching to second order. What is GIS? 
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 grid independence study? 
*Residuals charts decreasing (>> converging)
*Grid independant study: then you need to recompute your stuff on a refined grid. You reached the solution if your solution isn't influenced by the grid refinement. 
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 and I still didn't get the full idea of grid independent study, I have tried to refine my grid as best as I could. Do I have to do another very well done mesh and compare both answers or what?  Please check your email. Thanks dude. 
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Here is my mesh. Is it possible to do a 2nd order with it and is it converged enough. 
John..
The grid independent study is like this: You have to have different mesh faces: example 10.00020.00030.000 and fix a parameter you want to study like Cf, Cl, Cd if any this values change less than 5% from mesh 10.000 and 30.000 means that it won´t be any different if you do a mesh with 40.000 faces because you are going to get very similar results, so you considerer that the 30.000 faces is okay for what you are doing. hope it help you 
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read case & data from previous 1st order solution>> switch to 2nd order >> Initialize or don't(if you start from converged 1st order solution you will get faster convergence) >> compute and write your coeff in a different file. Load your 2 graphs in excel, or whatever... and compare  You don't need to generate a very fine grid: follow what RGRUIZ said 
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and in the max face size by default its 1.78m. can someone tell me the full steps of how to change mesh faces 10.00020.00030.000. 
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Very helpful understood you, and testing now... 
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