
[Sponsors] 
March 21, 2007, 14:50 
Lift and drag calculation

#1 
Guest
Posts: n/a

Hi,I am trying to calculate lift,drag and moment coefficient for a NACA0012 at different AOA.I ve runned the simulation and post processed the results in CFX.Apparently i ve got very good results.My problem is that i dont know which variable correspond to the lift and drag forces.I though it was 'Force Y' for lift and 'Force X' for drag,but I ve got very small values....E7 order...definetly too small.Can anyone suggest a proper way to find out my lift and drag forces? Thank you.
Franny 

March 21, 2007, 15:42 
Re: Lift and drag calculation

#2 
Guest
Posts: n/a

Hi, ForceY and ForceX (normalised by projected areas should give you Lift and Drag coefficients. I assume that your freestream flow is along X axis. If you are giving an angle of attack by changing the flow direction, you then need to take components perpendicular to and along flow direction respectively. Alternatively, you can extract the pressure values around the airfoil and integrate them to get the lift and drag forces. This will however not give you viscous drag. So the best option is still to use the ForceX and ForceY from CFX post. If you want to see viscous and pressure drag breakups, you can use Normal and Tangential ForceX and ForceY.
Shastri 

March 21, 2007, 16:53 
Re: Lift and drag calculation

#3 
Guest
Posts: n/a

Hi thank you for your message.Yes, the free stream is along the X direction and the angle of attack is given by changing the flow direction and not the wing position in the fluid domain. I ve extracted teh force in the X and Y direction by postprocessing my results and then i ve calculated the relative components along and perpendicular to the flow direction.Lift and Drag founded for each value of force X and Y as L=Fxsin(a0a)+Fycos(a0a) and D=Fxcos(a0a)+Fysin(a0a),integrated all over the airfoil but Cl is still very small(107 order). About the other method, using pressure distribution,to calculate Cl and Cd i assume i need to distinguish between lower and upper surface right? And finally,in the variable selection in CFX i ve decided for 'Force X' and 'Force Y',but you mention 'Normal and Tangential ForceX and ForceY'...do i have to try with that ones?


March 21, 2007, 17:50 
Re: Lift and drag calculation

#4 
Guest
Posts: n/a

Hi, the method of calculation seems alright. I would first check the units. You might have accidentally imported the mesh in mm or inches instead of meters. To calculate using pressure, yes, you need to distinguish between upper and lower surfaces. You can actually create a polyline that passes through the airfoil profile and export pressures on that polyline. You can later split the data in Excel/Matlab at points with Min and Max X for leading and trailing edges respectively. You can calculate the forces Fy and Fx and proceed to calculate as before. The normal and tangential components wont give you answers different than the regular ForceY and ForceX so that wont solve your problem if something is basically wrong in simulation itself. But you can use them to do a detailed study of your errors. I remember that you can extract them by choosing particular plot lines in the solver manager.
My first doubt would be on units so just check lengths, velocities etc are all as they should be. Hope this helps. Shastri 

March 21, 2007, 17:52 
Re: Lift and drag calculation

#5 
Guest
Posts: n/a

BTW, I hope you are deviding the Fy and Fx values by normalising factor (0.5* rho* u^2*chord*span). THAT gives the value of Cl and Cd, not the forces themselves.


March 22, 2007, 02:46 
Re: Lift and drag calculation

#6 
Guest
Posts: n/a

Hi Shastri,thank you very much for your help.Off course i m dividing the aerodynamic forces by the dynamic pressure,not problem about that.I will chech this morning about the unit of measure,but the value i ve got for the pressure on the polyline are reasonable,the plot as well and most important the boundary layer that i see above the wing is amazingly good....i can see all the velocity profile evolution along the surface till the small separation bubble.This is for me was a good sign that the simulation was right.I will check the units and i will let you know.Thank you again. Ciao
Franny 

March 22, 2007, 18:38 
Re: Lift and drag calculation

#7 
Guest
Posts: n/a

Guys,
I ran into an issue with the CFX POST function "Force", it only calculates the pressure forces (isotropic) and not the normal component of the viscous stress. This can give considerable errors. Use the .out file to get your results. 

March 23, 2007, 05:10 
Re: Lift and drag calculation

#8 
Guest
Posts: n/a

Hi Anil, thank you for your advise.This is what i ve found out yesterday.From my results file at the end of the simulation,i summed the pressure force to the viscous one and i ve obtained reasonable values for Cl and Cd.Unfortunately they looks like the half of what they should be.For a Naca0012 at 15 deg theory sais Cl=0.8, I ve got Cl=0.4.What do you think?
Franny 

March 23, 2007, 07:31 
Re: Lift and drag calculation

#9 
Guest
Posts: n/a

Franny,
As the factor is a round number like "2", do you have a factor 0.5 in the dynamic pressure, basically 0.5*rho*u*u? I would suggest use 'xfoil' results to compare your pressure distribution, if they match then you know it is the lift calculation formula. Anil 

April 15, 2007, 10:37 
Re: Lift and drag calculation

#10 
Guest
Posts: n/a

hi,will u please give me the exact procedure to find the drag in CFX post using pressuredistance graph.


April 24, 2014, 06:15 
Drag coefflcient calculation using Meshless method

#11 
New Member
hari poudyal
Join Date: Sep 2013
Location: Kathmandu,Nepal
Posts: 6
Rep Power: 12 
Hello everyone,
I am now trying to calculate drag coefficient using Meshless MPS method. I am now using Pressure for calculating drag coefficient but the result is not good. So, if anyone has idea about calculating drag coefficient,please share with me too. Your sincere Hari 

April 26, 2014, 07:23 

#12 
Super Moderator
Glenn Horrocks
Join Date: Mar 2009
Location: Sydney, Australia
Posts: 17,566
Rep Power: 141 
This is the CFX forum. No meshless MPS methods are being used here.


April 28, 2014, 00:24 
Drag coefficient for Meshless MPS method

#13 
New Member
hari poudyal
Join Date: Sep 2013
Location: Kathmandu,Nepal
Posts: 6
Rep Power: 12 
Dear ghorrocks sir,
Thank you very much for your response. Do you know any reference or any other MPS related papers about drag coefficient. I will be really thankful for your kindness. Your sincere Hari Poudyal 

April 28, 2014, 00:26 

#14 
Super Moderator
Glenn Horrocks
Join Date: Mar 2009
Location: Sydney, Australia
Posts: 17,566
Rep Power: 141 

April 28, 2014, 00:32 

#15 
New Member
hari poudyal
Join Date: Sep 2013
Location: Kathmandu,Nepal
Posts: 6
Rep Power: 12 
Dear ghorrocks sir,
I am working in MPS method since 1 year. I know MPS method ( but not too much). So, I am facing problem for calculating force from pressure distribution. ( just P = F /A is not sufficient.) Any way, thank you very much for your link. your sincere Hari Poudyal 

June 2, 2014, 03:36 

#16 
New Member
hari poudyal
Join Date: Sep 2013
Location: Kathmandu,Nepal
Posts: 6
Rep Power: 12 
Hello Everyone,
I am calculating drag coefficient. I found a fluent guide to calculate the drag coefficient. https://confluence.cornell.edu/displ...irfoil+Step+7 But I have a confusion about unit vector in drag force calculation. It has been written as "ed is the unit vector parallel to the flow direction". If the flow direction is along X axis, then can I use "ed" = (1,0,0) or should I calculate the instantaneous velocity component along X direction? If anyone has any idea, please share with me. Yours sincere Hari 

November 27, 2019, 14:47 
lift and drag coefficient for 3d airfoil

#17 
Member
Join Date: Aug 2018
Posts: 80
Rep Power: 7 
Hi, I am trying to calculate Cd and Cl for 3D airfoil having dimension 4c in spanwise direction, and free stream is in x direction . As I know, in Fluent I need to just select the direction vector as x=1 y=0 z=0 for drag coefficient and x=0, y=1 and z=0 for lift coefficient. I already have selected area in reference values. But in a video I have seen, it was changing the z value also. If I am wrong please correct me because I do not know much about 3D simulation. I t is my first 3D simulation.
Thank you! 

Thread Tools  Search this Thread 
Display Modes  


Similar Threads  
Thread  Thread Starter  Forum  Replies  Last Post 
Drag and Lift coefficient calculation  viraj  Main CFD Forum  0  February 5, 2010 06:41 
NACA 23020 airfoil drag and lift calculation.  Zmur  CFX  2  December 23, 2008 17:35 
Calculation of lift and drag coefficients  Prachi  CFX  3  August 14, 2007 15:05 
Correct lift but wrong pressure drag  possible?  zx  Main CFD Forum  4  July 28, 2007 00:38 
lift and drag calculation  actone  CFX  0  December 27, 2006 18:11 