Need Cl,Cd for high angles of attack

Poojitha · October 18, 2013, 06:07

Hi

I am a final year student working on numerical modelling of Darrieus turbine. I require Cl,Cd as a function of angle of attack for angles - 0 to 60 deg. Can you please direct me to a source where I can find experimental/any reliable Cl Cd values for some symmetric NACA profiles.

maazz · October 23, 2013, 13:44

http://aerospace.illinois.edu/m-seli..._database.html

Poojitha · October 24, 2013, 00:01

Thanks for replying

But I want Cl, Cd values of NACA airfoils for angles of attack 0-60 deg but I am finding results only for angles till 20deg and very few for NACA...Can u help?

October 18, 2013, 06:07	Need Cl,Cd for high angles of attack	#1
Poojitha New Member dynamic Join Date: Oct 2013 Posts: 3 Rep Power: 5	Hi I am a final year student working on numerical modelling of Darrieus turbine. I require Cl,Cd as a function of angle of attack for angles - 0 to 60 deg. Can you please direct me to a source where I can find experimental/any reliable Cl Cd values for some symmetric NACA profiles.

October 23, 2013, 13:44	UIUC airfoil database	#2
maazz New Member Muhammad Maaz Siddiqui Join Date: Jun 2013 Location: Karachi, Pakistan Posts: 3 Rep Power: 6	http://aerospace.illinois.edu/m-seli..._database.html

Thread Tools
Show Printable Version Email this Page
Display Modes
Linear Mode Switch to Hybrid Mode Switch to Threaded Mode

Similar Threads
Thread	Thread Starter	Forum	Replies	Last Post
NACA 0012 Different Angles of Attack	Arvind	CFX	10	March 18, 2014 17:43
Aerofoil at high angles of attack	bean	STAR-CCM+	3	January 28, 2013 12:15
much smoother Cd and Cl vs. angles of attack compared to experimental results	violet	FLUENT	0	June 17, 2009 14:52
Flows at High Angles of Attack	Sarah C.	FLUENT	2	March 18, 2009 08:39
Airfoil simulation in High Angles of Attack	Yasser Nabavi	FLUENT	0	April 21, 2006 17:28

October 24, 2013, 00:01		#3
Poojitha New Member dynamic Join Date: Oct 2013 Posts: 3 Rep Power: 5	Thanks for replying But I want Cl, Cd values of NACA airfoils for angles of attack 0-60 deg but I am finding results only for angles till 20deg and very few for NACA...Can u help?