Lift Force Estimation on Symmetric Aerofoils
Prototype
α = 6.0° ·
CL ≈ 0.63
Illustrative thin-aerofoil approximation with a post-stall drop-off — not the Ansys Fluent / Source Panel Method results.
Highlights
- Conducted simulations analyzing lift and drag forces under varying incident flow water velocities and sharp hydrodynamic angles of attack.
- Generated digital flow models in Ansys Fluent to mimic absolute boundary layers and fluid separations, writing an alternative numerical solver utilizing the Source Panel Method.
- Formulated data plots proving a positive linear correlation between the aerofoil's structural aspect ratio and absolute lift forces.
Technologies
- Ansys Fluent
- Source Panel Method
- Boundary Layer Modeling
- Lift & Drag Analysis