AE7745:3D airflow simulation and analysis using ANSYS CFD package

Formal feedback

 All assignments must be submitted by the date and time specified above.

Students are required to submit an electronic copy of their completed assignment via the Assignments section of Canvas and follow any specific instructions. Any change to this instruction will be advised via Canvas.

In line with Faculty policy for late submission of coursework, any work submitted up to a week late will be capped at 40%. Coursework submitted after this time will receive 0%.

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Please note that if you submit a piece of work you have judged yourself fit to undertake the assessment and cannot claim mitigating circumstances retrospectively.

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Module Learning Outcomes

The following module learning outcomes and professional body learning outcomes are tested in this assessment:

1. To provide comprehensive understanding on the fundamental theory and knowledge on the computational technologies and skills for modern aerospace system design and analysis, more specifically, the Finite Element Method (FEM) for structural integrity analysis and Computational Fluid Dynamics (CFD) method for fluid flow and heat transfer analysis. (AHEP4 LOs: M1)

2. To develop appropriate two- and three-dimensional models including geometry, boundary conditions, meshing and solution parameters and to interpret results from FEA analysis for design of aerospace systems using commercial FEA software. (AHEP4 LOs: M1 & M2)

3. To develop appropriate models and skills for CFD design and analysis of aerospace systems, including the complex turbulence modelling, by performing and critically assessing the results of a CFD analysis using commercial CFD software. (AHEP4 LOs: M1 & M2).

4. To build up and practice critical thinking and problem-solving skills applied to structural and aerodynamics analysis. (AHEP4 LOs: M2)

5. To communicate the advantages and limitations of FEA and CFD in aerospace design and analysis as a professional design engineer. (AHEP4 LOs: M2 & M5)

6. To practice the fluid-structure interaction (FSI) problem to understand further how the FSI will affect product design and performance in real applications. (AHEP4 LOs: M2 & M5)

Assessment task and specific terms

Specific details of the assessment task

Please refer to ‘Assignment Details’ at the end of the document. Specific submission requirements and the format of the submission
There are two pieces of submission:

Submission 1 (via the Assignments section of Canvas) - An electronic report including all details of your meshing, CFD simulation work and results postprocessing and analysis should be submitted to Canvas in PDF format only. Please avoid MS Word file submission on Canvas because of some formatting issues with equations/plots. Your work should be first fully word-processed (not handwritten and scanned) and then a copy saved as PDF for Canvas submission. The name of the file should be as follows: ‘AE7745_CW1_Retake_KUNumber.pdf’

Submission 2 (to oneDrive) - All your meshing, ANSYS solving and postprocessing related files, such as ANSYS Fluent, Fluent meshing and CFD-Post files should be compressed into one .zip file and upload to the designated OneDrive folder as below by the submission deadline. Please label your file clearly with your KU number.

Referencing and citation requirements
You are expected to refer to the indicative bibliography of the module provided in Canvas and the additional bibliographic sources suggested in the lecture notes. In addition, you must undertake your own appropriate further reading and research in relation to the matters addressed in this coursework brief. Evidence of independent reading and research will be rewarded. A list of References must be presented at the end of the report listing all bibliographic sources cited in Harvard style.

Assessment Criteria

Assessment of your submission will be based on the following weighted assessment criteria as given below which relate to the specified module and PSRB learning outcomes. Assessment criteria are reproduced in Canvas in a rubric.

Create and describe the ONERA M6 Wing (4);

physical description of the flow problem including flow conditions (3); identifying the source of the validation data (3). Create high-quality mesh around the model for an external flow simulation, detail and justify the key mesh generation process (10); describe the mesh properties (5) evaluate mesh quality corresponding to the flow physics (5) Perform compressible 3D external flow simulation in CFD solver, describe model setup, boundary conditions, turbulence modelling method, numerical schemes choice, convergence monitors, and etc (10); provide justifications for your settings (5); Check full convergence (5). 20 Present and post-process the CFD results, including all the typical flow variables to reflect the important flow physics

Complete in proper report format with neat and tidy presentation, starting with a front cover, contents & page numbers, main body and ending with references and appendices (if applicable), and submission of ANSYS CFD files. 

Academic skills support

For help and advice on this assessment please contact the assessment setter/s or the module leader. For advice on academic writing and referencing please contact the Faculty of Engineering, Computing and the Environment (ECE) Student Academic Success Centre (SASC). Trained staff and students will give you guidance and feedback on assessments. SASC can be accessed here

Assignment Details

Software requirement: ANSYS CFD package is required to complete this piece of work Specific requirements:

3D ONERA M6 Wing geometry model is used for following tasks:

1. Describe briefly the geometrical model using words, table, figures, and etc. you can refer to the resources website as listed as below. Source of validation data as included in the website needs to be identified.

https://www.grc.nasa.gov/www/wind/valid/m6wing/m6wing.html

3D ONERA M6 Wing geometry model with sharp TE is available in here (The geometric model of the wing can be cut as a blunt trailing edge to ease the mesh generation effort):

3D ONERA M6 Wing Validation for Turbulence Model Numerical Analysis (nasa.gov)

1. Provide a physical description of the flow problem, including determining the flow conditions and flow type.
2. Create a high-quality mesh based on the geometric model, detail the key meshing processes, such as the flow domain, mesh resolution, mesh type, mesh size, mesh count and mesh quality. Demonstrate the final mesh including zoom-in details in local area. Details for the mesh parameters calculation is not necessary, online grid spacing tools can be used to determine the meshing parameters.
3. Perform a 3D steady flow simulation using ANSYS CFD solver Fluent for your case. Describe and justify CFD model setup and solution control settings. Check and justify simulation full convergence.
4. Present results using proper post-processing tool CFD Post; Present shock wave occurrence and development on top and bottom wing surface; pressure and velocity contours, boundary layer flow separation if available, turbulence flow development, and etc.
5. Validate CFD results against the chosen validation data. Cp data at all cross sections over the wing should be validated and discussed properly.
6. Discuss your results (this must be a technical discussion) and finally draw a technical conclusion. All plots should be completed in Excel or CFD-Post.

Summary of Assessment Requirements

Students are required to complete a full CFD analysis of the 3D ONERA M6 Wing using ANSYS Fluent, supported by a high-quality mesh, rigorous simulation setup, and validation of results against NASA reference data. The submission consists of:

1. Written PDF Report (Submission 1)

The report must include:

• Description of the ONERA M6 Wing geometry, with figures/tables

• Identification of validation data sources (NASA website)

• Physical description of the flow problem (flow type, Mach number, angle of attack, conditions)

• High-quality mesh creation, including:

  • Flow domain selection

  • Mesh generation method

  • Mesh type, resolution, mesh count

  • Mesh quality justification

  • Zoom-in images of key regions

• 3D compressible steady-state CFD simulation setup in Fluent:

  • Boundary conditions

  • Turbulence model

  • Numerical schemes

  • Convergence strategy and checks

  • Justification of settings

• Post-processed results:

  • Shock-wave patterns

  • Pressure & velocity contours

  • Boundary layer/separation (if present)

  • Turbulence behaviour

• Validation of Cp distributions at all wing sections using NASA data

• Technical discussion of findings and a conclusion

• Proper formatting: cover page, contents, references (Harvard), appendices

2. ANSYS Folder Submission (Submission 2)

A ZIP file containing:

• Meshing files

• Fluent solver files

• CFD-Post results

How the Academic Mentor Would Guide the Student 

Below is a structured explanation of how an academic mentor would help the student approach this assignment efficiently and correctly.

Step 1: Understanding the Task and Learning Outcomes

The mentor first helps the student interpret:

• Purpose: build competency in FEA/CFD modelling, turbulence modelling, mesh generation, and technical reporting.

• Expected skills:

  • Geometry interpretation

  • CFD workflow

  • Critical thinking

  • Professional engineering communication

The student learns what must be shown to meet the rubric: accurate CFD work, validation, and structured reporting.

Step 2: Breakdown of ONERA M6 Wing Geometry Requirements

The mentor instructs the student to:

• Visit the NASA ONERA M6 wing validation page

• Extract geometry dimensions, planform details, sweep angle, aspect ratio, span, and chord distribution

• Insert diagrams and tables into the report

• Identify the source of validation Cp data for credibility

This ensures the student starts with reliable, referenced geometric inputs.

Step 3: Explaining the Physical Flow Problem

The mentor guides the student to:

• Identify flow conditions (Mach 0.839, Reynolds number, AoA commonly 3° or as specified)

• Describe type: 3D steady compressible turbulent external flow

• Discuss expected phenomena:

  • Shock formation

  • Boundary layer behaviour

  • Flow separation zones

This forms the theoretical foundation for the simulation.

Students are required to complete a full CFD analysis of the 3D ONERA M6 Wing using ANSYS Fluent, supported by a high-quality mesh, rigorous simulation setup, and validation of results against NASA reference data. The submission consists of:

1. Written PDF Report (Submission 1)

The report must include:

• Description of the ONERA M6 Wing geometry, with figures/tables

• Identification of validation data sources (NASA website)

• Physical description of the flow problem (flow type, Mach number, angle of attack, conditions)

• High-quality mesh creation, including:

  • Flow domain selection

  • Mesh generation method

  • Mesh type, resolution, mesh count

  • Mesh quality justification

  • Zoom-in images of key regions

• 3D compressible steady-state CFD simulation setup in Fluent:

  • Boundary conditions

  • Turbulence model

  • Numerical schemes

  • Convergence strategy and checks

  • Justification of settings

• Post-processed results:

  • Shock-wave patterns

  • Pressure & velocity contours

  • Boundary layer/separation (if present)

  • Turbulence behaviour

• Validation of Cp distributions at all wing sections using NASA data

• Technical discussion of findings and a conclusion

• Proper formatting: cover page, contents, references (Harvard), appendices

2. ANSYS Folder Submission (Submission 2)

A ZIP file containing:

• Meshing files

• Fluent solver files

• CFD-Post results

 

 

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