Objective:-
To study compressible flow in a converging diverging nozzle i.e, supersonic flow, normal shock, mach no distribution, fluid velocity distribution, Density distribution, pressure distribution, temperature distribution, effective viscosity distribution, total stagnation pressure distribution etc through out the CD nozzle.
Converging diverging nozzle is axisymmetry with inlet radii = 0.02432 m, throat radii = 0.005 m and outlet radii = 0.008 m respectively. Length of CD nozzle = 0.14 m. This analysis is carried out for both full volume of CD nozzle as well as quarter section volume of CD nozzle.
(But Fluid 141 - 2D fluid-thermal element is also used for initial meshing of area to get fine mesh through out the full volume of CD nozzle)
Full volume of CD nozzle
Quarter section volume of CD nozzle
Fluid 141 - 2D fluid-thermal element is used in both type of volumes only to get fine meshing not included in analysis
Full volume of CD nozzle
Quarter section volume of CD nozzle
Path selected for graph results is between Node_1 (at the inlet section of axisymmetry) and Node_1401 (at the outlet section of axisymmetry) in both volume types
Density animations and graph
Full volume of CD nozzle
Density is continuously decreasing even after the throat
Quarter section volume of CD nozzle
Graph is continuously increasing in between region of throat and exit
There is no significant loss of fluid velocity in between the region of throat and exit, hence no conversion of kinectic energy into enthalpy due to normal shock
Here, total stagnation pressure decrease upto certain region after throat could be due to irreversibility cause by normal shock.
There is no sudden rise in temperature in between region of throat and exit, hence there is no conversion of kinetic energy into enthalpy due to normal shock
No rise in pressure after throat region
As, it can seen in pressure graph, mach no graph, fluid velocity graph, temperature graph and density graph of full volume of CD nozzle that is no significant changes in between the region of throat and exit which shows presence of normal shock except in case of total stagnation pressure graph it's irreversibility is needed to study further. Overall it can be considered that back pressure must be less than exit pressure, hence normal shock might be formed outside the diverging section(exit).
Ansys analysis obtained values can be verified at throat condition using following formulas :-
Full volume analysis values are more convincing.
Thank you
Happy to discuss more in detail.
Guide me and let me know my mistakes