Hello there, can anyone lemme know where I can kind lift/drag values for Naca 0012 airfoil at Re more than 500000....any angle of attack is fine with me...any paper citing from ur side would be of a great help...since I need them urgently

try using Xfoil code, it has good correlation with experimental data .

Actaully I need a published paper to validate my data....I know abt xfoil...but need a paper to compare....thanks anyway for replying

.J Thibert, M. Grandjacques, and L.H. Oham, "NACA 0012 Airfoil", AGARD Advisory Report, 1979.

N. Gregory and O.L. O'Reilly, "Low Speed Aerodynamic Characteristics of NACA0012 Airfoil Section, Including the Effects of Upper Surface Roughness Simulation Hoarfrost", NPL Aero Report 1308, National Physical Laboratory 1970.

I think one of the these reports will have what you are looking for.

Reagrds

James Date

Hi,

I am unable to solve the tutorial file given in fluent- aerofoil , compressible flow problem. Mach number=0.8.

I followed the instruction given in tutorial but i was unable to get the solution.

can you give your idea how to solve compressible flows.

bye san

Thanks Mr.James...thanks man...i will check out for that papers