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GP-AE-1LLG1AKAerospaceReady

OpenFOAM airfoil aerodynamic validation

An OpenFOAM v2606 NACA 0012 validation study at Reynolds number 6 million, covering three meshes, seven angles, lift, drag, surface pressure, wall resolution, and NASA comparison.

OpenFOAM airfoil aerodynamic validation project visual
GP-AE-1LLG1AK · Aerospace
  • OpenFOAM v2606
  • Python 3
  • Matplotlib

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

Airfoil CFD results depend on domain size, mesh quality, near-wall resolution, turbulence treatment, numerical schemes, convergence, and reference data. A single contour plot cannot establish aerodynamic accuracy.

Project objectives

  • Generate the NACA 0012 geometry and O-grid from reviewed source.
  • Run three mesh levels at 0 and 10 degrees.
  • Calculate lift, drag, moment, y+, residuals, and surface pressure.
  • Run an angle study from -4 to 15 degrees.
  • Compare selected coefficients with NASA numerical reference values and state every material limitation.

Project structure

Project components

01

Geometry and meshing

Generates a closed-trailing-edge NACA 0012 surface, a 20-chord circular farfield, radial grading, empty front and back patches, and strict mesh checks.

02

OpenFOAM solver

Runs potential-flow initialisation, first-order settling, and second-order steady incompressible RANS with Spalart-Allmaras.

03

Study runner

Builds and solves all 11 declared cases from one versioned JSON case matrix.

04

Evidence extractor

Calculates last-20-sample force means, coefficient stability, y+, residuals, mesh quality, and owner-cell surface Cp.

05

Validation

Compares 0, 10, and 15 degree coefficients with NASA Table 7.4 and records percentage differences.

Methodology

Project workflow

  1. 01
    Generate

    Python writes native OpenFOAM dictionaries and fields for the declared angle and mesh.

  2. 02
    Check

    Every case must pass checkMesh with all geometry and topology checks enabled.

  3. 03
    Solve

    Potential flow is followed by first-order and then second-order simpleFoam stages.

  4. 04
    Extract

    Forces, pressure, y+, residuals, and mesh metrics are converted to JSON, CSV, PNG, and SVG evidence.

  5. 05
    Validate

    Mesh trends, symmetry, stability, and NASA reference errors are interpreted together.

Demonstration scenario

The NACA 0012 airfoil is solved on three grids at 0 and 10 degrees, then across a medium-grid angle sweep from -4 to 15 degrees. The student uses force histories, Cp plots, y+, mesh trends, and NASA errors to explain what the model predicts and where it remains limited.

Engineering

Tools and method

Tools
The project uses OpenFOAM v2606, Python 3, Matplotlib for subject analysis, simulation, and results.
Case format
Native OpenCFD OpenFOAM v2606 dictionaries, fields, blockMesh topology, function objects, and solver logs.
Flow model
Steady two-dimensional incompressible external aerodynamics at Reynolds number 6 million using Spalart-Allmaras.
Mesh method
Programmatic NACA 0012 circular O-grid with 2,688, 5,760, and 10,752 cells.
Analysis
Python extracts coefficient histories, surface Cp, y+, residuals, reference errors, tables, tests, and 17 repeatable figures.

Testing

Evaluation

Evaluation measures

  • All three grid levels pass strict checkMesh checks
  • Fine-mesh 10-degree lift coefficient of 1.03989, 5.1 percent below the NASA value
  • Fine-mesh 10-degree drag coefficient of 0.01880, 52.1 percent above the NASA value
  • Fine-mesh zero-degree drag coefficient of 0.009196, 12.0 percent above the NASA value
  • Symmetric lift at positive and negative 4 degrees
  • Seven automated tests passing

Project boundaries

  • Only OpenCFD OpenFOAM v2606 cases are delivered.
  • The study is steady, two dimensional, incompressible, and limited to the documented NACA 0012 case at Reynolds number 6 million.
  • The mixed y+ range and continuing drag change mean drag is not grid independent.
  • Steady RANS does not establish the physical stall angle.
  • The output is not flight-test, aircraft-design, or certification evidence.

Included

  1. 01Programmatic NACA 0012 geometry and circular O-grid workflow
  2. 02Three mesh levels with 2,688, 5,760, and 10,752 cells
  3. 03Eleven completed steady RANS cases from -4 to 15 degrees
  4. 04Lift, drag, moment, Cp, y+, residual, and mesh-quality evidence
  5. 05NASA numerical comparison at 0, 10, and 15 degrees
  6. 0617 labelled figures in PNG and SVG with raw JSON and CSV results
  7. 07Complete project files, models, calculations, and analysis material in a private GitHub repository
  8. 0880-page project documentation in PDF and editable Word formats
  9. 099-page setup and usage guide

Project record

No information is collected on this page.

Permanent project ID
GP-AE-1LLG1AK
Catalogued
22 Aug 2026
Completed
23 Aug 2026
Verified
23 Aug 2026
Demonstration
Included in repository

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.