[hhhhe]

Hi

I would like to evaluate thrust from a nozzle exit. Using Ansys Fluent, how would you go by integrating these expressions:

Massflow = Int rho U_x dA

thrust = Int ( rho U_x^2 + p ) dA

where rho is the density, U_x is the axial velocity, p is the static pressure, and A is the area. All of these should be evaluated at the nozzle exit.

Can you enter your own expressions to be integrated with Ansys Fluent?

Note that I'm using a 2D axisymmetric nozzle configuration.