pressure. lift and drag coefficients
 

I am M. Sc. Engineering student. I am working on project, " Aerodynamics analysis of aerofoil (NACA 0012) using cfd code." I am using Fluent Code and so far i have found velocity and pressure distribution for 0, 3, 8, 12 and 16 angles of attack at Reynolds Nos. 3.3e5, 6.6e5, 1.3e6 for compressible flow(air). Now i want to find pressure , lift and drag coefficients so I need guidance calculating these coefficients using results obtained from Fluent code (pressure distribution). For the verification of my results i also need data related to my project. My postal address is Waqar Mahboob, C--230, CNS Hostels, P. O. Nilore Islamabad, Pakistan. Thanks in anticipation.