High CL lift coefficient in Stall Angle of attack airfoil -- CFD Online Discussion Forums

April 26, 2016, 21:27	High CL lift coefficient in Stall Angle of attack airfoil	#1
restuesaputra New Member Anggie Restue Saputra Join Date: Apr 2016 Posts: 3 Rep Power: 10	I did a flow simulation over airfoil NACA 0015 using ansys fluent. Everything is ok in values of CL and CD for AoA 0 degree till 10 degree. But when i did simulation in AoA 15 degree values of CL is very high arround 1, it should be the value of CL in this AoA is low arround 0.4 cause 15 degree is near the stall angle (due to experiment result). Whats wrong with my simulation? Thanks before

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
Ffd_control_point_2d	feiyi	SU2	4	September 30, 2019 13:42
Lift Coefficient vs Angle of Attach for Pitching Airfoil	fkanyako	FLUENT	3	July 16, 2014 08:35
Lift Coefficient vs Angle of Attach for Pitching Airfoil	fkanyako	Fluent UDF and Scheme Programming	0	January 29, 2014 04:17
Analysis of angle of attack vs lift generated	vikhattangady	FLUENT	0	October 31, 2013 05:42
Lift Coefficient Vs. Angle of Attack	cfd_pro	Main CFD Forum	1	August 23, 2002 18:21

All times are GMT -4. The time now is 17:20.