CFD Simulations of Shock Patterns Downstream of a Rocket Nozzle
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This webinar focuses on conducting a computational fluid dynamic simulation to understand the flow patterns downstream of a supersonic Rocket engine. The main objective of this webinar is to demonstrate how computational methods can be used to understand flow patterns within problems that are difficult to simulate experimentally.
Successful rocket design involves accurately estimating the thrust generated by it's nozzle. The thrust parameter however, is dependent on the ambient pressure and the pressure within the combustion chamber of the rocket. Developing an experimental set up to accurately measure the thrust produced for a supersonic nozzle is a challenging task. With computational tools, it is relatively easy to simulate the same flow phenomena on a computer. Once a computational setup is created to replicate a given nozzle profile, the same setup can be used to understand the nozzle's performance for varying ambient pressure encountered at different altitudes. The thrust profile thus determined can be used in estimating the rocket's orbit for a given payload. In the webinar, we will generate a geometry in Ansys Spaceclaim and generate a structured mesh using blocking technology. The mesh will be solved in Ansys Fluent to capture relevant flow phenomena.
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