Ansys CFX – CD Nozzle (De Laval Nozzle)

Written by cfd.ninja

March 11, 2020

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Source: NASA

A nozzle is a relatively simple device, just a specially shaped tube through which hot gases flow. Ramjets and rockets typically use a fixed convergent section followed by a fixed divergent section for the design of the nozzle. This nozzle configuration is called a convergent-divergent, or CD, nozzle. In a CD nozzle, the hot exhaust leaves the combustion chamber and converges down to the minimum area, or throat, of the nozzle. The throat size is chosen to choke the flow and set the mass flow rate through the system. The flow in the throat is sonic which means the Mach number is equal to one in the throat. Downstream of the throat, the geometry diverges and the flow is isentropically expanded to a supersonic Mach number that depends on the area ratio of the exit to the throat. The expansion of a supersonic flow causes the static pressure and temperature to decrease from the throat to the exit, so the amount of the expansion also determines the exit pressure and temperature. The exit temperature determines the exit speed of sound, which determines the exit velocity. The exit velocity, pressure, and mass flow through the nozzle determines the amount of thrust produced by the nozzle.

In this tutorial you will learn to simulate a CD Nozzle using ANSYS Fluent. First, we will import the points and then we will generate the mesh using a structured mesh in Ansys Meshing. You can download the file in the following link.

Ansys CFX – NACA 4412 (Structured Mesh)

Ansys CFX – NACA 4412 (Structured Mesh)

The NACA four-digit wing sections define the profile by:
First digit describing maximum camber as percentage of the chord.
Second digit describing the distance of maximum camber from the airfoil leading edge in tenths of the chord.

OpenFOAM vs ANSYS CFX

OpenFOAM vs ANSYS CFX

OpenFOAM is the free, open source CFD software developed primarily by OpenCFD Ltd since 2004. It has a large user base across most areas of engineering and science, from both commercial and academic organisations.

We share the same tutorial using ANSYS CFX.

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Ansys CFX – NACA 4412 (Structured Mesh)

Ansys CFX – NACA 4412 (Structured Mesh)

The NACA four-digit wing sections define the profile by:
First digit describing maximum camber as percentage of the chord.
Second digit describing the distance of maximum camber from the airfoil leading edge in tenths of the chord.

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