Assuming level flight, LIFT = WEIGHT,...........
Lift Coefficient (CL) = L / (1/2 x rho x V^2 x S)
rho = density of air at sea level I guess (cant remember off hand, but might be something like 1.22506 I think - its been a while)
V = velocity (m/s)
S = wing area (includes portion "masked" by fuselage)
L = Weight = M x g (g = 9.81, M = Mass)
My calculator dont work, but give this a try!!!
FP