ERROR: End AOA in airfoil table too small k 1 i 1 in Fluent 6.3 -- CFD Online Discussion Forums

September 8, 2010, 07:53	ERROR: End AOA in airfoil table too small k 1 i 1 in Fluent 6.3	#1
Asela New Member Asela Kandamby Join Date: Sep 2010 Posts: 1 Rep Power: 0	Hi everyone, i am using fluent 6.3 and i'm trying in generating results for a 2 bladed helicopter having 2 sections. I have the sectional lift and drag arranged in the .dat files which is similar to the standara format used in the NACA 0015. My AOA varies from -20 to 26 degrees. When i run it on Fluent i seem to get this error no matter how much i change the format. Does anyone have a idea on the matter? Thanks

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
Fluent 6.3 Tut 12: Dynamic mesh	RolandP	FLUENT	23	August 10, 2023 05:25
Fluent 6.3 32bit vs Fluent 12.0 64bit	ibex7	FLUENT	7	April 18, 2011 03:44
Airfoil Ice Accretion Modelling Using Fluent	Virk	FLUENT	0	July 27, 2009 07:48
Convergence in Fluent at small (order 1) Re	Sergei Chernyshenko	FLUENT	0	January 10, 2008 06:39
Time Step Size for Airfoil Model - Fluent	Prateek	Main CFD Forum	0	November 4, 2004 19:42

All times are GMT -4. The time now is 07:23.