Sonic Boom Reduction Analysis: Concorde CFD Simulation
Budget / Salary$30–250
TypeFreelance project
LocationRemote
Posted3 hours ago
ANSYS Fluent CFD Simulation – Concorde Nose Geometry Modification for Sonic Boom Reduction
Project Overview
I am looking for an experienced Aerospace Engineer or CFD Specialist to assist with my undergraduate graduation project, which investigates the effect of nose geometry modifications on sonic boom generation in a supersonic aircraft, using the Concorde as a case study.
The project will use ANSYS Workbench and ANSYS Fluent to simulate supersonic flow around a simplified Concorde-like aircraft geometry and investigate how different nose shapes affect shock waves, pressure signatures, and aerodynamic performance.
Two research papers and my graduation project proposal will be provided as technical references.
Scope of Work
1. Geometry Preparation
* Prepare or modify a simplified Concorde-like 3D aircraft geometry.
* Create a baseline configuration and several modified nose geometries.
* Investigate selected nose parameters, such as nose length, bluntness, and nose radius.
* Prepare the geometry for CFD simulations in ANSYS Workbench.
2. Computational Domain and Mesh Generation
* Create a suitable computational domain for supersonic external flow.
* Generate an appropriate mesh to capture shock waves and pressure gradients around the aircraft nose.
* Apply local mesh refinement in critical regions.
* Perform mesh quality checks and, where feasible, a mesh-independence study.
* Explain the selected mesh strategy and boundary conditions.
3. ANSYS Fluent Simulations
* Set up and run compressible supersonic flow simulations.
* Use appropriate operating conditions based on the provided research papers and project proposal.
* Select suitable governing equations, air properties, pressure-based or density-based solver settings, and numerical schemes as appropriate for the problem.
* Evaluate an appropriate turbulence model or inviscid Euler approach, with technical justification.
* Obtain converged and physically meaningful solutions for the baseline and modified configurations.
4. Results and Comparative Analysis
* Generate Mach number contours and static pressure contours.
* Visualize shock waves and compare their locations and strengths.
* Extract pressure distributions and near-field pressure signatures at suitable locations.
* Calculate and compare aerodynamic coefficients, including drag coefficient (CD) and lift coefficient (CL) where applicable.
* Compare all nose configurations against the baseline geometry.
* Discuss the trade-off between sonic boom-related pressure characteristics and aerodynamic performance.
5. Sonic Boom Propagation – If Feasible
* Assess whether the extracted near-field pressure signatures can be used with an appropriate sonic boom propagation tool, such as NASA PC-Boom or another suitable validated method.
* If this stage is included, provide the required input data, propagation results, and a comparison of ground-level pressure signatures.
* Clearly identify any limitations or additional software requirements.
Required Deliverables
1. ANSYS Workbench project files and Fluent case/data files.
2. Baseline and modified CAD geometry files.
3. Mesh files and documented mesh settings.
4. Simulation results for all agreed configurations.
5. High-quality plots, contours, and comparison graphs.
6. A technical report describing the methodology, solver setup, boundary conditions, mesh strategy, convergence, results, and conclusions.
7. A short explanation of how to open the project and reproduce the simulations.
Required Qualifications
* Demonstrated experience with ANSYS Fluent and ANSYS Workbench.
* Strong background in aerospace CFD and compressible flow.
* Experience with supersonic or hypersonic flow and shock-wave analysis.
* Familiarity with CFD mesh generation, convergence assessment, and aerodynamic coefficient calculations.
* Experience with sonic boom prediction or aeroacoustic pressure-signature analysis is highly desirable.
Important Notes
Please review the attached proposal and research papers before submitting your offer.
In your proposal, please specify:
* Your relevant ANSYS Fluent and supersonic CFD experience.
* The proposed simulation methodology and software requirements.
* The number of geometries and simulation cases included in your price.
* The expected computational requirements and estimated completion time.
* Which deliverables are included in your offer.
* Whether sonic boom propagation to ground level is included or quoted separately.
Please provide examples of relevant previous CFD projects, if available.
The work should be technically sound, reproducible, and suitable for an undergraduate aerospace engineering graduation project. I also need to understand the methodology and results so I can explain and defend the project academically.
Project Overview
I am looking for an experienced Aerospace Engineer or CFD Specialist to assist with my undergraduate graduation project, which investigates the effect of nose geometry modifications on sonic boom generation in a supersonic aircraft, using the Concorde as a case study.
The project will use ANSYS Workbench and ANSYS Fluent to simulate supersonic flow around a simplified Concorde-like aircraft geometry and investigate how different nose shapes affect shock waves, pressure signatures, and aerodynamic performance.
Two research papers and my graduation project proposal will be provided as technical references.
Scope of Work
1. Geometry Preparation
* Prepare or modify a simplified Concorde-like 3D aircraft geometry.
* Create a baseline configuration and several modified nose geometries.
* Investigate selected nose parameters, such as nose length, bluntness, and nose radius.
* Prepare the geometry for CFD simulations in ANSYS Workbench.
2. Computational Domain and Mesh Generation
* Create a suitable computational domain for supersonic external flow.
* Generate an appropriate mesh to capture shock waves and pressure gradients around the aircraft nose.
* Apply local mesh refinement in critical regions.
* Perform mesh quality checks and, where feasible, a mesh-independence study.
* Explain the selected mesh strategy and boundary conditions.
3. ANSYS Fluent Simulations
* Set up and run compressible supersonic flow simulations.
* Use appropriate operating conditions based on the provided research papers and project proposal.
* Select suitable governing equations, air properties, pressure-based or density-based solver settings, and numerical schemes as appropriate for the problem.
* Evaluate an appropriate turbulence model or inviscid Euler approach, with technical justification.
* Obtain converged and physically meaningful solutions for the baseline and modified configurations.
4. Results and Comparative Analysis
* Generate Mach number contours and static pressure contours.
* Visualize shock waves and compare their locations and strengths.
* Extract pressure distributions and near-field pressure signatures at suitable locations.
* Calculate and compare aerodynamic coefficients, including drag coefficient (CD) and lift coefficient (CL) where applicable.
* Compare all nose configurations against the baseline geometry.
* Discuss the trade-off between sonic boom-related pressure characteristics and aerodynamic performance.
5. Sonic Boom Propagation – If Feasible
* Assess whether the extracted near-field pressure signatures can be used with an appropriate sonic boom propagation tool, such as NASA PC-Boom or another suitable validated method.
* If this stage is included, provide the required input data, propagation results, and a comparison of ground-level pressure signatures.
* Clearly identify any limitations or additional software requirements.
Required Deliverables
1. ANSYS Workbench project files and Fluent case/data files.
2. Baseline and modified CAD geometry files.
3. Mesh files and documented mesh settings.
4. Simulation results for all agreed configurations.
5. High-quality plots, contours, and comparison graphs.
6. A technical report describing the methodology, solver setup, boundary conditions, mesh strategy, convergence, results, and conclusions.
7. A short explanation of how to open the project and reproduce the simulations.
Required Qualifications
* Demonstrated experience with ANSYS Fluent and ANSYS Workbench.
* Strong background in aerospace CFD and compressible flow.
* Experience with supersonic or hypersonic flow and shock-wave analysis.
* Familiarity with CFD mesh generation, convergence assessment, and aerodynamic coefficient calculations.
* Experience with sonic boom prediction or aeroacoustic pressure-signature analysis is highly desirable.
Important Notes
Please review the attached proposal and research papers before submitting your offer.
In your proposal, please specify:
* Your relevant ANSYS Fluent and supersonic CFD experience.
* The proposed simulation methodology and software requirements.
* The number of geometries and simulation cases included in your price.
* The expected computational requirements and estimated completion time.
* Which deliverables are included in your offer.
* Whether sonic boom propagation to ground level is included or quoted separately.
Please provide examples of relevant previous CFD projects, if available.
The work should be technically sound, reproducible, and suitable for an undergraduate aerospace engineering graduation project. I also need to understand the methodology and results so I can explain and defend the project academically.
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