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

Cp values for F3 rear wing for a 4th year thesis

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

Reply
 
LinkBack Thread Tools Display Modes
Old   October 15, 2004, 02:51
Default Cp values for F3 rear wing for a 4th year thesis
  #1
Joe Bryant
Guest
 
Posts: n/a
Hey,

i am interested to know by setting an area of the aerofoils of a rear wing value in reference areas does that at all interact with calculating the pressure coefficient of say of an 3d aerofoil section.

I noticed that i haven't touch the reference values and i know that when i calculate lift an drag which i will do from the pressure coefficents i have to add the area into it however do i need to do anything to the pressure coeffient (i.e.) incorporate area.

as cp= p -p_inf / (0.5 x density x velocity^2)

also i am only modelling half the rear wing so does that mean that when i calculate lift and drag i only use the area of half the wing (i.e. the two aerofoil elements) and is the area just the reference area of the aerofoil shapes i.e. span x chord. or is it the frontal area, any help would be greatly appreciated. very much so.

cheers joe bryant
  Reply With Quote

Old   October 15, 2004, 03:36
Default Re: Cp values for F3 rear wing for a 4th year thes
  #2
Luca Cavagna
Guest
 
Posts: n/a
Hi Joe! the surface area you should use is the HALF planform surface of the full-wing since you're using half of the real model. The cp value doesn't depend on the reference area. Only the drag and the lift coefficient depend since they come from the sum of the product betwen the element area and its cp (projected then along the direction you specificed; for ex.(1,0,0)). CL=net AERO_FORCE/(0.5 density vel^2 S) I hope to be clear. Luca
  Reply With Quote

Old   October 15, 2004, 03:42
Default Re: Cp values for F3 rear wing for a 4th year thes
  #3
Joe
Guest
 
Posts: n/a
Thank you so much for your help its much appreciated.

Cheers Joe Ps. will put you as an acknowledgement in my 4th year thesis for aeronautical engineering Sydney University

cheers once again
  Reply With Quote

Old   October 15, 2004, 06:37
Default Re: Cp values for F3 rear wing for a 4th year thes
  #4
Luca Cavagna
Guest
 
Posts: n/a
You're welcome...if you had any problem with Fluent just write!I'd be glad to give you some suggestions (if I can...). Luca
  Reply With Quote

Old   June 10, 2010, 23:40
Default
  #5
New Member
 
Shreyas
Join Date: Jun 2010
Posts: 7
Rep Power: 7
shreyas is on a distinguished road
Quote:
Originally Posted by Luca Cavagna
;115554
You're welcome...if you had any problem with Fluent just write!I'd be glad to give you some suggestions (if I can...). Luca

Hey luca...how do I get the values of cp in the right range...I get it in the range of 1e6 etc...I need to compare it with theoretical results
shreyas 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
Question about reference values --> Area (multi element wing) Zweeper FLUENT 7 March 28, 2010 11:29
[Other] Question about aerodynamik design (rear wing) Zweeper ANSYS Meshing & Geometry 1 March 23, 2010 09:35
Study of a Rear wing Crazer FLUENT 2 August 10, 2009 03:45
Wing Drag Values Ed Reed FLUENT 1 November 16, 2004 17:30
help needed about phase change Yanhu Guo Main CFD Forum 4 January 24, 2001 00:16


All times are GMT -4. The time now is 06:51.