Comparative CFD analysis of hypersonic airfoil configurations using ANSYS Fluent
Mach 1–6 • Shockwave Analysis • Aerodynamic Optimisation • Mesh Validation
This project investigates the aerodynamic performance of multiple hypersonic airfoil geometries under compressible flow conditions using ANSYS Fluent.
The investigation compares:
- Double-Wedge Airfoil
- Bi-Convex Airfoil
- Dome Airfoil
across Mach 1 to Mach 6 flow regimes.
The study focuses on:
- shockwave behaviour
- pressure distribution
- drag characteristics
- solver convergence
- aerodynamic optimisation
- CFD validation methodologies
- ANSYS Fluent
- SolidWorks
- MATLAB
- Density-based solver
- Compressible flow modelling
- Structured mesh generation
- Mesh independence study
- Convergence validation
- Hypersonic Aerodynamics
- Shockwave Analysis
- Pressure Distribution
- Drag Optimisation
- Solver Stability Investigation
Detailed CFD results, contour plots, convergence studies, and validation outputs are included in the appendix report.
Varun Saini
Aerospace Engineering Graduate
Preston, United Kingdom