Cp over an airfoil using fluent

info_bahaider · July 10, 2010, 08:35

How to calculate/determine the Cp at upper and lower surface of an airfoil at user-defined points (at upper and lower surface), instead of cslculating Cp at each grid point (cell/node).

I have experimental data at some certain locations, I want to compare at those locations.

How can I do this either by using Fluent or tecplot?

Regards

Ali

kdrbrk · July 13, 2010, 03:13

maybe you can define upper and lower surface as different walls.
than you can plot Cp for both surfaces and you can compare with experimental data.

July 10, 2010, 08:35	Cp over an airfoil using fluent	#1
info_bahaider New Member ALi Join Date: Aug 2009 Posts: 9 Rep Power: 16	How to calculate/determine the Cp at upper and lower surface of an airfoil at user-defined points (at upper and lower surface), instead of cslculating Cp at each grid point (cell/node). I have experimental data at some certain locations, I want to compare at those locations. How can I do this either by using Fluent or tecplot? Regards Ali

Similar Threads
Thread	Thread Starter	Forum	Replies	Last Post
[Commercial meshers] Fluent3DMeshToFoam	simvun	OpenFOAM Meshing & Mesh Conversion	50	January 19, 2020 15:33
Fluent 12.0 is worst then Fluent 6.2	herntan	FLUENT	5	December 14, 2009 02:57
solving ocean wave with Fluent or CFX?	gholamghar	Main CFD Forum	1	March 21, 2009 12:49
how to creat a mesh in fluent for airfoil	sanjay umarani	FLUENT	0	March 7, 2005 05:26
Fluent equation error?!?	TOM	FLUENT	6	July 15, 2002 03:24

July 13, 2010, 03:13		#2
kdrbrk Member Burak Join Date: May 2009 Posts: 90 Rep Power: 16	maybe you can define upper and lower surface as different walls. than you can plot Cp for both surfaces and you can compare with experimental data.