Hi all,

I am running a test case of NACA - 0012 airfoil at zero angle of attack and Re=5000 for an incompressible flow. I am not able to validate my results, as the validation data is not available with me. I am in need of the data like, sfc, cp and drag, for the above mentioned test case. I request the community to help me in getting the data or the link from which i can download the data.

thanks in advance...

-snegan

Hi all,

If any one know abt the flow feature characteristics for this test case like: 1: Flow will separate or not? as we have seen only the compressible flow results, its not conclusive whether the flow will seperate in an incompressible flow. 2: The seperation distance from the leading edge of the airfoil. 3: Any computational results if any one come across, i think it will be more useful for my validation.

Ill be grateful if u can help me in this regard... Thanks in advance...

-snegan

Here's a couple good ones.

Thibert, J.J. and Grandjacques, M. and Ohman, L.H., NACA0012 Airfoil,AGARD Advisory Report, 1979.

Gregory, N. and O'Reilly, O.L., Low Speed Aerodynamic Characteristics of NACA0012 Airfoil Section, Including the Effects of Upper Surface Roughness Simulation Hoarfrost,National Physical Laboratory,1970, No 1308.

I. H. Abbott and A. E. Von Doenhoff, Theory of Wing Sections, Dover Publications Inc, New York, 1959.

simple yahoo image search NACA0012 yields:

http://engapplets.aoe.vt.edu/fluids/vpm/naca0012.gif http://engapplets.aoe.vt.edu/fluids/vpm/vpmex.html http://flab.eng.isas.ac.jp/member/ts...rch/kaynak.jpg