#RocketEngineSimulation #FluidDynamics #CFD

Dear Engineers,

A rocket engine nozzle typically consists of a combustion chamber set at a very high pressure and temperature. The flow then accelerates through the nozzle, reaching a supersonic (higher than the speed of sound) value at the exit of the nozzle. This is the driving mechanism which accelerates rockets into space. Nozzles for rockets are designed for a specific thrust using the Method of Characteristics, a very popular engineering tool.

Here is a detailed tutorial explaining how to perform a compressible flow CFD (computational fluid dynamic) simulation through a rocket engine nozzle in 2D, using the ANSYS Fluent CFD software. This tutorial takes you through the whole process of designing a rocket nozzle namely: Flow conditions, Geometry (created in SOLIDWORKS), boundary conditions, meshing, setting up, solving the CFD, and postprocessing (CFD Post).

Without a doubt, meshing is undoubtedly the most challenging part of the simulation. Keep in mind as compressible flows normally have shocks and detached flow situations, as a result the mesh needs to be highly accurate and preferably structured (i.e each element can be located with coordinates).
To achieve this, use the Number of Divisions, Bias, Element Quantity features which are embedded in ANSYS. You need to select the nozzle wall, inlet region, throat, and outlet region sections and set the elements individually. To facilitate this, you will need to use the 'Face Split' feature in the Geometry section to break up your domain into a number of sections.

Best Wishes,
VDEngineering

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