
[Sponsors] 
August 12, 2011, 22:49 
lift and drag ceofficient problem

#1 
Member
iswadi
Join Date: Feb 2010
Posts: 44
Rep Power: 9 
i have done my analysis on my wing.
it was run at 2 different conditions. 1st condition was set at 15m/s velocity speed. 2nd condition was set at 10 m/s velocity speed. the main value that i am trying to get was the lift and drag coefficient (CL and CD).i have adopted almost the same step as the CFX airfoil tutorial provided in the Ansys customer portal. below was the formula that i adopted from the tutorial AOA = 10[deg] Denom = 0.5*massFlowAve(Density)@Inlet*Uinf^2*9.045[m]*0.001[m] Drag = cos(AOA)*Fx+sin(AOA)*Fy Fx = force_x()@Airfoil Fy = force_y()@Airfoil Lift = cos(AOA)*Fysin(AOA)*Fx Uinf = 10[m s^1] Ux = Uinf*cos(AOA) Uy = Uinf*sin(AOA) cD = Drag/Denom cL = Lift/Denom the problem that i`m facing now is the final results for lift and drag coefficient values for both condition (15m/s and 10m/s) are same!! i knew it was incorrect. i`m completely stuck right now. i dont know where was my mistake. can anybody give me some idea where i should start in tracing my mistake. FYI, my analysis was involving a FSI/ multifield analysis. 

August 13, 2011, 04:55 
urgently need....How To Calculate Friction Drag in CFX13

#2 
New Member
Ronald Hutauruk
Join Date: Dec 2010
Posts: 4
Rep Power: 8 
Dear Friends,
do you have some tutorials how to calculate friction drag in ansys CFX13. I need information for calculating viscous drag including pressure drag and friction drag in catamaran (demi hull) thx hutaru Indonesia 

August 14, 2011, 16:04 


#3 
Member
Mauricio Labarca
Join Date: Aug 2009
Posts: 35
Rep Power: 9 
Hello ice,
I'm not sure why you are getting those results but have you tried comparing the values of the data you're getting from your flow field in both cases? that'd be massFlowAve(Density)@Inlet, force_x()@Airfoil force_y()@Airfoil. I'm guessing you already compared all the other values ( Denom, Lift, Drag, etc.) hutaru:Can't help you with that, but open a new thread and maybe someone else will. 

August 15, 2011, 00:56 

#4 
Member
iswadi
Join Date: Feb 2010
Posts: 44
Rep Power: 9 
dear mauricio,
i have made comparison of force_x()@Airfoil and force_y()@Airfoil at 15m/s and 10m/s. indeed, there were huge different between them. the denom was constant. however i have made a manual calculation but still maintaining and used the value of force_x()@Airfoil and force_y()@Airfoil from computational. i was surprising to see that the formula below giving me a quite different value in manual results compare to computational results!! Drag = cos(AOA)*Fx+sin(AOA)*Fy Lift = cos(AOA)*Fysin(AOA)*Fx one more thing. i have gone through some of the posts in this forum. some of them were mentioned about Force_y () @Airfoil is equal to LIft ? Force_x () @Airfoil is equal to Drag ? is it true? do anybody have experienced in this situation? do anybody have their own formula in determining the LIFT and DRAG? Please share with me... Last edited by icemaniac178; August 15, 2011 at 04:05. 

August 15, 2011, 18:48 


#5  
Member
Mauricio Labarca
Join Date: Aug 2009
Posts: 35
Rep Power: 9 
Quote:
about the forces. As far as i know The force command operates on a boundary condition and gets the resultant force of all the nodes you have in the surface that makes your BC. My guess is that You'd have check the theory on how those Fx and Fy are supposed to be applied and obtained, one thing are the forces applied in one point of the airfoil, and another a balance obtained over the whole surface. 

August 16, 2011, 23:37 

#6 
Member
iswadi
Join Date: Feb 2010
Posts: 44
Rep Power: 9 
thanx mauricio,
i will check about the angle in radian unit. by the way, i have checked the theory about lift and drag coefficient. it really make sense where the theory says that the lift coefficient is almost constant when Re increase more than 10,000. Only Clmax is really affected due to Re changes. Drag coefficient also affected but only at minimum magnitude. Cd changes is more clearly when the Re <10,000. Anybody who have experienced on this matter is highly appreciated to share their knowledge. i believe this would be benefits to all 

August 17, 2011, 18:40 

#7  
Super Moderator
Glenn Horrocks
Join Date: Mar 2009
Location: Sydney, Australia
Posts: 13,201
Rep Power: 103 
Quote:


Thread Tools  
Display Modes  


Similar Threads  
Thread  Thread Starter  Forum  Replies  Last Post 
Lift and Drag Monitor Point Values Converging to Zero  Josh  CFX  24  May 9, 2011 10:38 
Lift and Drag ???  Yogibear  STARCCM+  4  June 20, 2010 10:11 
Correct lift but wrong pressure drag  possible?  zx  Main CFD Forum  4  July 27, 2007 23:38 
Zero Coefficient of Lift Problem  MH  FLUENT  0  February 25, 2007 12:48 
drag and lift coefficient  Noé  CDadapco  5  July 13, 2004 10:21 