CFD Online Logo CFD Online URL
www.cfd-online.com
[Sponsors]
Home > Forums > Main CFD Forum

How to plot Cp Vs X/c

Register Blogs Members List Search Today's Posts Mark Forums Read

Reply
 
LinkBack Thread Tools Display Modes
Old   July 24, 2012, 09:56
Default How to plot Cp Vs X/c
  #1
New Member
 
Abhipray Jain
Join Date: Mar 2012
Posts: 8
Rep Power: 7
abhiprayj is on a distinguished road
Hi,
I am trying to plot Cp Vs x/chord ... I tried to get the data from fluent but im not able to plot it .. I think i got the wrong data ... I went to XY plot and took headsail and headsail shadow and write the file and after opening it on excel i plot the graph which is wrong .. same i did for mainsail and mainsail shadow....plz help me its important .. moreover .. i saw in many other thesis .. their y axis says Cp and x axis says x/c but on x axis values are 0, 0.2, 0.4, 0.6, 0.8, 1.0.
whereas if i plot same thing on fluent v6, it shows me somewhat right graph but with negative values of Cp on the y axis .. im very confused plz help me...
abhiprayj is offline   Reply With Quote

Old   March 28, 2017, 02:58
Talking
  #2
New Member
 
Aron Chand
Join Date: Mar 2017
Posts: 1
Rep Power: 0
aaron chand is on a distinguished road
Quote:
Originally Posted by abhiprayj View Post
Hi,
I am trying to plot Cp Vs x/chord ... I tried to get the data from fluent but im not able to plot it .. I think i got the wrong data ... I went to XY plot and took headsail and headsail shadow and write the file and after opening it on excel i plot the graph which is wrong .. same i did for mainsail and mainsail shadow....plz help me its important .. moreover .. i saw in many other thesis .. their y axis says Cp and x axis says x/c but on x axis values are 0, 0.2, 0.4, 0.6, 0.8, 1.0.
whereas if i plot same thing on fluent v6, it shows me somewhat right graph but with negative values of Cp on the y axis .. im very confused plz help me...
Cp is pressure coefficient and x/c also known as x/chord is; x=x coordinate distance of the specific point or tap from the leading edge, c=chord length. So if your point one is 2mm from the leading edge and your chord length is 100, therefore your x/c value is 2/100 i.e. 0.02. Note that the max value of x/c is 1 because at 1, x=c.

Different airfoils with different angle of attack will plot different graphs. Always know the Cp value can never exceed Positive 1 because when Cp=1, that is the stagnation point and at that point the velocity of the particles will be infinitesimally small or approx. zero. But it can never be practically zero on the dot because this is a dynamic system. There is a MS-Dos program made my MIT, its called XFOIL. LEarn its command, and it can tell you the exact graph for most of the airfoil at any angle of attack
aaron chand is offline   Reply With Quote

Reply

Thread Tools
Display Modes

Posting Rules
You may not post new threads
You may not post replies
You may not post attachments
You may not edit your posts

BB code is On
Smilies are On
[IMG] code is On
HTML code is Off
Trackbacks are On
Pingbacks are On
Refbacks are On


Similar Threads
Thread Thread Starter Forum Replies Last Post
Plot on a curve Monica FLUENT 1 July 11, 2012 00:24
How to plot xy-Y plot of certain nodes maple2012 FLUENT 0 November 5, 2011 11:00
A girl fail to plot velocity profile when mesh changes + Wall function asherah STAR-CCM+ 0 February 19, 2010 18:45
Transfer low-res graphic file plot to excel plot quarkz Main CFD Forum 3 April 9, 2009 13:54
graph plot anindya Main CFD Forum 2 September 17, 2003 12:00


All times are GMT -4. The time now is 08:45.