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For this project a convergent-divergent (CD) nozzle will be analyzed in Ansys Fluent. The basic concept behind the nozzle geometry is to accelerate the flow by a convergent style geometry until mach 1 is achieved, the geometry then become divergent so as to further accelerate the flow in the supersonic regime (Figure 1). The challenges I saw from this project are focused on the location of the shock wave; this model assumes steady and uniform flow going into the nozzle but one can easily see how this is made much more complicated when modeling a real nozzle where perturbations and variable flow due to combustion must be accounted for.
Figure 1 - Converging-Diverging Nozzle Geometry
The next step was to mesh the geometry, as you can see from Figure 2, the mesh elements are very un-deformed and the mesh is very concentrated around the nozzle throat. You can also see that the mesh was created to be parallel to the expected position of the streamlines.
Figure 2 - Mesh
Figure 3,4 and 5 along with Graph 1 and 2 show the results from the Fluent calculation. The results follow the expected behavior as previously discussed; the flow accelerates in the convergent section, reaches Mach 1 at the throat, and then further accelerates down the divergent section. The pressure is inversely proportional to the velocity as expected from Bernoulli's equation.
Figure 3 - Pressure Contour
Figure 4 - Velocity Contour
Figure 5 - Velocity Vectors
Graph 1 - Pressure along x-direction Plot
Graph 2 - Velocity along x-direction Plot
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