If the coefficient of lift had a number, it would help.
600 times 3 = 1800. That's easy.
The co-efficient of lift is dimensionless.
Lift = 1/2 * density of air (rho) * velocity squared * wing area * Coefficient of lift.
Lift is in Newtons (a force, which has units kg*m/s^2)
density is kg/m^3
velocity squared is (m/s)^2
area is m^2
Multiply those last three together and you get (kg/m^3)*[(m/s)^2]*m^2
or kg*m/s^2 - the same units as lift, so the CL is dimensionless.
If you look up graphs of CL vs angle of attack you find that it's varies with the wing design, but is typically around 1.0 at typical angles of attack (5-10 degrees).
See
https://commons.wikimedia.org/wiki/File:LiftCurve.gif
Paul