Lift and Drag Coefficient data for NACA 2412 Airfoil
 

Hello

I am trying to find Lift and Drag Coefficient for NACA 2412 airfoil using S-A model. Now I need some standard data of Cd and Cl at different Angle of Attack for this airfoil to validate my results. If anyone have these data please respond here or mail me at mahbub.me.buet@gmail.com.

Thank you in advance.

Hi!

You can find wind tunnel data for lift, drag and moment coefficients for many NACA profiles in
I. H. Abbot and A. E. Von Doenhoff, Theory of wing sections.

If you are unable to obtain a copy of this book I can send you a screenshot
of lift and drag plots.

Seljak,

It would be great if you send me a screenshot for NACA 2412. I got a copy of Theory of Wing Section but that is not legible enough.

Thank you.

Oh, I meant screenshot of plots from this book. Unfortunately I don't have any other data.

Can you send me the screen shot of this book please?

Dear all,

I am calculating ship resistance in Fluent. anybody can explain for me what and how are equation of Force and Coefficient of force in Fluent Report?
any advise is welcome to email : Ducminh207@gmail.com

Fundamentals of Aerodynamics by John D Anderson, is a great book for NACA 2412 airfoil data.

Thank you very much Mr. Mahbub Islam

Hi, GreogorS, can you please send me a screenshot of NACA 0012 and 0015 drag and lift coefficients (for different angles of attack)? really appreciate it, thanks.

"Theory of Wing Sections: Including a Summary of Airfoil Data (Dover Books on Physics) by Ira H. Abbott, A. E. von Doenhoff" is available for free download at www.library.nu

and do u have the standard data CI and CD of NACA 2412 in different attack angles now? if u do, and can u send it to me? thank u so much
my Email is liubgs1989@gmail.com

Hi, GreogorS.
If you still have that book (I. H. Abbot and A. E. Von Doenhoff, Theory of wing sections.) can you please send me a screenshot of NACA 0021 drag and lift coefficients for different angles of attack?
I'll be thankful.


I just found this link that can help about lift coefficient and drag coefficient for different angles of attacks. http://mac6.ma.psu.edu/VAWT/Sand80-2114.pdf

You don't know how to use google search, do you?

If you are intrested in the lift and drag coefficients of airfoils you can try "javafoil" (see link below)
http://www.mh-aerotools.de/airfoils/javafoil.htm
there it is possible to do variations of the angle of attack and you can export the geometry as a textfile, which you can use for CAD-import.

Have fun ;-)

Look in the Theory of Wing Section by Abbott