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August 29, 2005, 06:39 |
lift & drag coefficient on airfoil
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#1 |
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dear sirs how can i calculate the lift & drag coefficient on airfoil surface for 2-d incompressible case, for fluent post processing i can calculate and draw only cp(pressure coefficient), what about lift & drag coefficient ?? thanks in advance for your early replay
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August 29, 2005, 07:26 |
Re: lift & drag coefficient on airfoil
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#2 |
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You can monitor lift & drag coefficients while your solution iterates by going to Solve->Monitors->Forces. In fact, if in your final results you want the lift & drag coefficient, then you should monitor them to ensure convergence.
Once you have a final solution you can get forces and moments from Report->Forces. It will print the force (or moment) in your units and in coefficient terms. Make sure you've defined your reference values at Report->Reference values. A sticking point is that "length" is the reference length used in the moment coefficient (Cm = 1/2*Rho*V^2*Aref*Lref) while "depth" is the length of your model in the z direction. If you set "depth" to 1, then it's a per unit length setup. Hope this helps, and good luck, Jason |
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October 23, 2009, 02:59 |
dear sir..
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#3 |
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vivit
Join Date: Oct 2009
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Can you tell me?? What is the Basic Calculation of FLUENT on Computing Lift Coef In Modelling 2D??
thanks |
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October 23, 2009, 19:38 |
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#4 |
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teguh hady
Join Date: Aug 2009
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Hy vivit apriliyanti!!
My problem is same as yours!! I think that 2d airfoil don't have A!!! So if A equal to 0 then Cl will be infinite!!! But when we run FLUNT 2D we'll see VOLUME after check our grid!!! the value of volume is not zero!! I think the value of Cl is based on that volume!! hope it helps!! teguhtf |
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December 7, 2009, 07:25 |
hello mister
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#5 |
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vivit
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wahat is grid independensi in FLUENT? please you explain,thnks
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December 16, 2009, 08:22 |
Basic Computation Of 2D
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#6 |
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teguh hady
Join Date: Aug 2009
Location: Saga, Japan
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Sorry, for waiting. After searching in some books, I've opinion that For solving Cl & Cd in 2D. There is assumption that the value of A is 1. you can read this on Anderson Computational Fluid Mechanics And Heat Transfer.
Hope it helps teguhtf
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December 16, 2009, 11:14 |
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#7 | |
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JT.Q
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Quote:
2、in force report panal, you can set the force vector to obtain cd and cl respectively.set x=1 and y=0,you will get cd,if x is the velocity direction.set y=1 and x=0, you will get cl. |
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December 17, 2009, 09:30 |
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March 31, 2015, 20:02 |
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#9 | |
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Quote:
I am simulating the flow over a 2 element airfoil which is to say that there is a main wing and a flap. I want all coefficients to be scaled to a unit chord. I am unsure whether FLUENT uses the real length of the airfoil or the reference length. I calculate both the lift and drag coefficient on the main, flap and both. However only the main wing and flap combined chord is 1m. I am not quite clear from your explanation what whether FLUENT is assuming a unit chord for all calculations of CL and CD regardless of actual size or if it assumes the actual size. Depth is the z direction or the span of the wing and the length is used for moment how do I define a unit chord? is it in the area value? Thanks in advance for the help. |
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