Home > Forums > Software User Forums > ANSYS > FLUENT

How to find Line Cp at different wing spans-0.44, 0.80, 0.95 in fluent?

Updated Threads

Reply

Search this Thread

November 11, 2017, 14:49	How to find Line Cp at different wing spans-0.44, 0.80, 0.95 in fluent?	#1
FluidAerodynamics New Member California Join Date: Nov 2017 Posts: 2 Rep Power: 0	Hello, I am trying to find Cp at different spans of a 3d wing airfoil- 0.2, 0.44, 0.8, 0.95. I do not how to find the both x-points of the chord. Please help ASAP. I could do the 0.2 Cp because both the x points at the chord ends were known, But I don't know the same for the different spans. Please let me know asap.!

Reply

Tags

airfoil., coefficient of pressure, fluent, wing, wing chord

« Previous Thread | Next Thread »

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 Off Pingbacks are On Refbacks are On Forum Rules

Similar Threads
Thread	Thread Starter	Forum	Replies	Last Post
[blockMesh] error message with modeling a cube with a hold at the center	hsingtzu	OpenFOAM Meshing & Mesh Conversion	2	March 14, 2012 09:56
OpenFOAM 1.7.1 installation problem on OpenSUSE 11.3	flakid	OpenFOAM Installation	16	December 28, 2010 08:48
[blockMesh] BlockMeshmergePatchPairs polyTopoChanger	benru	OpenFOAM Meshing & Mesh Conversion	3	June 29, 2008 21:24
Errors running allwmake in OpenFOAM141dev with WM_COMPILE_OPTION%3ddebug	unoder	OpenFOAM Installation	11	January 30, 2008 20:30
error while compiling the USER Sub routine	CFD user	CFX	3	November 25, 2002 15:16

All times are GMT -4. The time now is 20:26.