C Grid Mesh for Aerofoil Analysis -- CFD Online Discussion Forums

June 4, 2018, 00:17	C Grid Mesh for Aerofoil Analysis	#1
brok9n New Member Join Date: Jun 2018 Posts: 2 Rep Power: 0	Hey guys, I'm attempting to analyse a NACA0009 aerofoil, my end goal is to determine lift and drag coefficients for a range of AOA. So far I have made a 2d unstructured c-grid mesh (using ICEM) and have imported it into Fluent. However, when attempting to solve I get the following error. "pressure-far-field boundary conditions can only be used with ideal gases" Attempting to fix the error, all I can find on google is setting the working fluid to an ideal gas, which I have done without any luck. I'd appreciate any assistance.

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
decomposePar problem: Cell 0contains face labels out of range	vaina74	OpenFOAM Pre-Processing	37	July 20, 2020 05:38
Gambit problems	Althea	FLUENT	22	January 4, 2017 03:19
Grid refinement ratio for unstructured mesh	oj.bulmer	FLUENT	4	March 4, 2013 10:18
[snappyHexMesh] snappyHexMesh won't work - zeros everywhere!	sc298	OpenFOAM Meshing & Mesh Conversion	2	March 27, 2011 21:11
How to mesh the 1st grid point?	Daniel	Main CFD Forum	1	October 8, 2007 02:27

All times are GMT -4. The time now is 05:29.