2d nozzle simulation, need help
 

I am currently conducting a project of simulating supersonic flow in a nozzle in 2d.
My problem is how to define the area of the inlet and outlet of the nozzle, since the reporting surface area is incorrect.

For example, the inlet has a diameter of 21mm, hence the actual area should be A=D^2 x pi /4 = 3.46E-4. But the reporting surface area is 21mm^2, which leads to an incorrect reporting mass flowrate too.

How do i change the surface area so that the reporting area, mass flowrate will be correct?

Thanks in advance

supersonic flow analysis of 2D Nozzle
 

Are you using any software for the simulation ? if yes which software are you using. In software you need not calculate any areas. I have done a similar project using Fluent on a C-D nozzle considering the upper half since is axi-symmetric. In such case area should be equal to radius(r)*depth(d) and since the depth is unity so area is equal to r m^2.

If you can tell me about the type of nozzle you have chosen and other details I can help you further.

Seems like your software is unaware of your geometry being axisymmetric, and treats it as planar of unit thickness.

Looking for qualified freelancer to simulate supersonic flow through C-D nozzle using fluent 6.2.16

please contact upal_arif@yahoo.com