Hi.

I hope to simulate NACA0012 airfoil numerically at low Reynolds in laminar flow.

B.C. my code is incompressible code.

So I tried to search some numerical/experimental datas(like Cp, Cl, Cd) of NACA0012 at low Reynolds and laminar flow.

But mainly the reference datas are results of Compressible flow (numerically)at Mach=0.8 or 0.5.

So How to get the reference value of NACA0012 airfoil at low Reynolds in laminar flow ?

Here's two useful refs for NACA 0012 data:

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

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

Regards James

Hi there,

1)- Check the following webpage:

http://www.unibas.it/utenti/bonfiglioli/node10.html

It might be useful if you want to validate the viscous terms of your code. There are some velocity profile available.

Keep in mind that these are only numerical results that Bonfiglioli performed.

2)- Also check the following paper: Yu D, Mei R, Shyy W. "A multi-block lattice Boltzmann method for viscous fluid flows". Int. J. Numer. Methods Fluids Vol 39, pp 99–120, 2002

They apparently evaluated their numerical scheme by computing the flow around a NACA 0012 for Re=500; 1000, 2000, and 5000.

Again, these are numerical results and not experimental data.

Hope this might help. Good luck

Frederic Felten