Compressible Flow in a Nozzle

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One of the most common application of a converging-diverging nozzle is in a supersonic wind tunnel. The inlet flow into the converging section is subsonic and as the cross sectional area of the converging section decreases, the flow velocity increases until it reaches sonic condition at the throat. In the diverging section of the nozzle, the flow is accelerated further such that the flow velocity at the nozzle exit is the required Mach Number at the test section. Another critical application of converging-diverging nozzle is in the area of propulsion, where it is designed to generate the required thrust and assist in the maneuverability of the aircraft or rocket. In this regard, it is important to analyze the flow within the nozzle and reduce the total pressure losses. In this tutorial, you will learn how to setup the simulation to analyze the flow through the nozzle by creating the geometry of the nozzle, meshing the geometry and setting up the physics and numerical model. This SimCafe Fluids Course was developed by Dr. Rajesh Bhaskaran at Cornell University in partnership with Ansys. It serves as an e-learning resource to integrate industry-standard simulation tools into courses and provides a resource for supplementary learning outside the classroom.

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