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GP-AE-0S9SET7AerospaceOpen for request

OpenFOAM supersonic nozzle simulation

An OpenFOAM-only compressible-flow study of choking, expansion, shocks, pressure ratio, and thrust in a converging-diverging nozzle.

  • OpenFOAM v2606
  • ParaView
  • Gmsh
  • Python
  • Docker

Software compatibility

OpenFOAM v2606 only

Cases are prepared for the OpenCFD OpenFOAM v2606 distribution. No ANSYS Fluent, COMSOL, STAR-CCM+, or OpenFOAM Foundation v14 files are included.

Project definition

Problem statement

Nozzle pressure, temperature, Mach number, shock position, and thrust change nonlinearly with area ratio and back pressure, while compressible CFD is sensitive to mesh and numerical dissipation.

Project objectives

  • Model a selected axisymmetric or planar converging-diverging nozzle.
  • Simulate choked, underexpanded, overexpanded, and internal-shock operating cases.
  • Compare centreline and station properties with one-dimensional isentropic and normal-shock theory.
  • Perform mesh and time-step or iteration-sensitivity checks.
  • Calculate pressure and momentum thrust under clearly stated boundaries.

System design

System modules

01

Nozzle model

Defines geometry, area distribution, gas properties, total conditions, back pressure, and reference stations.

02

Compressible cases

Configures density-based or coupled compressible OpenFOAM runs and stability controls.

03

Theory calculator

Calculates area-Mach, isentropic, critical, and normal-shock reference quantities.

04

Flow analyser

Extracts Mach, pressure, temperature, mass flow, shock position, and thrust terms.

05

Verification study

Compares CFD with theory across meshes and operating pressure ratios.

Methodology

System workflow

  1. 01
    Verify geometry

    The area distribution and analytical design condition are calculated.

  2. 02
    Run design case

    A baseline compressible simulation establishes choking and exit conditions.

  3. 03
    Vary back pressure

    Prepared cases move through subsonic, shock-containing, and supersonic regimes.

  4. 04
    Check numerics

    Mesh, conservation, residual, and shock-resolution effects are compared.

  5. 05
    Compare theory

    Station properties, mass flow, shock location, and thrust are evaluated against theory.

Demonstration scenario

The same nozzle is run at design and elevated back pressures. The design case reaches the predicted supersonic exit condition, while another forms an internal shock. CFD station values and shock position are compared with the analytical model.

Engineering

Technical architecture

Case format
Native OpenCFD OpenFOAM v2606 compressible cases with scripted parameter changes.
Gas model
A documented calorically perfect or selected thermophysical gas model within its valid range.
Numerics
Shock-capable schemes, controlled initialisation, stability monitoring, and mesh refinement near expected gradients.
Analysis
Python theory and extraction scripts plus ParaView state files for Mach and pressure fields.

Testing

Evaluation

Evaluation measures

  • Mass-flow conservation and choking behaviour
  • Mach, pressure, and temperature error at reference stations
  • Shock-location and pressure-jump error
  • Mesh and numerical-scheme sensitivity
  • Momentum, pressure, and total thrust consistency
  • Runtime and stability across pressure ratios

System boundaries

  • Only OpenCFD OpenFOAM v2606 cases are delivered.
  • Combustion, reacting chemistry, real-gas effects, ablation, and structural heating are excluded.
  • Thrust depends on the stated gas and boundary assumptions.
  • The project is not a rocket-engine or propulsion-system design approval.

Included

  1. 01Parametrised converging-diverging nozzle geometry
  2. 02OpenFOAM compressible-flow case files
  3. 03Analytical, shock-location, and thrust comparison scripts
  4. 04Prepared meshes, pressure-ratio cases, and results
  5. 05Complete source code in a private GitHub repository
  6. 06Complete project documentation with synopsis, abstract, methodology, nozzle equations, CFD setup, validation results, screenshots, and conclusion
  7. 07Setup and usage guide

Project record

No buyer information is collected on this page.

Permanent project ID
GP-AE-0S9SET7
Catalogued
22 Aug 2026
Completed
Pending
Verified
Pending
Demonstration
Added when ready

Handover

After purchase

  1. 01
    Payment is confirmed

    The project is marked unavailable and cannot be purchased again.

  2. 02
    Repository access is granted

    The buyer's submitted GitHub account receives access to the private repository.

  3. 03
    The purchase record is delivered

    The certification sheet is prepared from the reviewed buyer details and sent privately by email.