UAV Wing Design Thesis Package
Budget: ₹1,500 – ₹12,500 INR
I’m ready to commission a full MTech-level thesis—complete with a polished PowerPoint deck—on the experimental analysis and optimization of UAV wing design, integrating both CFD simulation and sub-sonic wind-tunnel testing.
Scope of study
The manuscript must assess aerodynamics, structural integrity, and material selection in tandem. On the aerodynamic side, I need a deep dive into lift and drag coefficients, stall characteristics, and flow-separation behaviour. Multiple wing plans (straight, tapered, swept, etc.) should be modelled, tested, compared, and the best configuration justified through a clear optimisation routine.
Research approach
Employ a rigorous research methodology: literature survey, problem definition, model creation, mesh-independence checks, CFD runs (ANSYS Fluent or OpenFOAM are acceptable), followed by physical validation in a sub-sonic wind tunnel. Present the correlation between numerical and experimental results, discuss discrepancies, and refine the model accordingly. Structural and material analyses can use standard FEA packages (e.g., Ansys Mechanical) or an equivalent open-source alternative, provided the reasoning is explicit.
Deliverables & acceptance criteria
• Complete thesis document, formatted to MTech guidelines, with all chapters, figures, references, raw data appendices, and editable source files.
• 25–30 slide PowerPoint summarising objectives, methodology, key findings, comparative results across wing designs, and final recommendations.
• CFD and FEA project files, cleanly organised for repeatability.
• Wind-tunnel test logs, measurement sheets, and calibration proof.
• Final optimisation summary showing how each design iteration improved target metrics.
I’ll review once for technical depth, originality (plagiarism check will be run), and coherence between simulation and experimental sections. Timelines and intermediate milestones can be discussed right away—looking forward to collaborating.
Scope of study
The manuscript must assess aerodynamics, structural integrity, and material selection in tandem. On the aerodynamic side, I need a deep dive into lift and drag coefficients, stall characteristics, and flow-separation behaviour. Multiple wing plans (straight, tapered, swept, etc.) should be modelled, tested, compared, and the best configuration justified through a clear optimisation routine.
Research approach
Employ a rigorous research methodology: literature survey, problem definition, model creation, mesh-independence checks, CFD runs (ANSYS Fluent or OpenFOAM are acceptable), followed by physical validation in a sub-sonic wind tunnel. Present the correlation between numerical and experimental results, discuss discrepancies, and refine the model accordingly. Structural and material analyses can use standard FEA packages (e.g., Ansys Mechanical) or an equivalent open-source alternative, provided the reasoning is explicit.
Deliverables & acceptance criteria
• Complete thesis document, formatted to MTech guidelines, with all chapters, figures, references, raw data appendices, and editable source files.
• 25–30 slide PowerPoint summarising objectives, methodology, key findings, comparative results across wing designs, and final recommendations.
• CFD and FEA project files, cleanly organised for repeatability.
• Wind-tunnel test logs, measurement sheets, and calibration proof.
• Final optimisation summary showing how each design iteration improved target metrics.
I’ll review once for technical depth, originality (plagiarism check will be run), and coherence between simulation and experimental sections. Timelines and intermediate milestones can be discussed right away—looking forward to collaborating.