Interactive computational engineering with actual solvers and 3D visualization.
Research Question
Can AI-assisted engineering workflows move from model setup through computation, visualization, verification and reusable interactive engineering applications?
Problem
Engineering simulation typically requires specialized desktop software, significant setup time, and expertise in both the physical domain and the computational tool. The gap between having an engineering question and getting a useful computational answer remains wide for preliminary analysis, education, and rapid design iteration.
Why It Matters
- Rapid preliminary aerodynamic assessment during concept design
- Interactive engineering education and visualization
- Democratizing access to computational engineering tools
- Browser-based simulation reducing infrastructure requirements
- Integration of computation into larger engineering workflows
Current Approach
The VLM Aerodynamics Simulator implements a Vortex Lattice Method solver with interactive 3D visualization:
- NACA airfoil generation — Parametric wing geometry from standard designations
- VLM computation — Python/NumPy solver computing lift and induced drag
- Pressure visualization — Color-mapped Cp distribution on 3D wing surface
- Interactive controls — Real-time angle-of-attack adjustment with live coefficient updates
Methodological Scope
The Vortex Lattice Method is a potential-flow method suitable for preliminary aerodynamic analysis. It assumes inviscid, incompressible flow and provides lift and induced drag estimates. It is not equivalent to full Navier-Stokes CFD and does not capture viscous effects, flow separation, or turbulence.
Results are appropriate for conceptual design comparison and educational demonstration, not for detailed engineering certification.
Limitations
- VLM is potential-flow only — not full CFD
- Cannot model viscous effects, separation, or turbulence
- Results not validated against experimental wind-tunnel data
- Suitable for preliminary analysis and education only
- Single wing planform; no fuselage or multi-body interactions