Compressible Flow Through a Converging Nozzle - Simulation Example

Overview

Jet engines provide thrust to propel an aircraft forward. The amount of thrust generated is directly proportional to the velocity difference between the outgoing gases and the incoming air. In order to impart high velocities to the exhaust gases from the combustion chamber, engines are fitted with devices called nozzles. Exhaust gases expand as they flow through the nozzle, i.e., the pressure decreases and, consequently, the velocity increases. In this example, we will examine the flow behavior of air through a converging nozzle, operating at a nozzle pressure ratio of 2.

Objectives

In this simulation example, you will learn how to simulate a compressible air flow through a converging nozzle. You will also learn how to calculate variables such as thrust and discharge coefficient, and compare them with the experiments.

Setup

Download the Mesh file required for setting up the simulation and associated Case and Data files here. Follow the instructions below to set up this simulation in Ansys Fluent starting with the Mesh file. In case you face any issues setting up or running the simulation, refer to the corresponding initial and final Case and Data files.

Alternate video link.

Results and Discussion