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The Source Panel Method

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Owen James Weisenberger

Project Timeline

Jan 2025 - May-2026

OVERVIEW

This project developed a MATLAB solver for the numerical source panel method based on equations from Anderson’s book. The source panel method approximates the flow around an object using discrete panels, which are essential for modeling nonlinear geometries. A NACA 0012 airfoil was analyzed at two angles of attack, demonstrating how streamlines curve around the airfoil. This method provides an efficient approach to understanding complex aerodynamic flow fields, offering a valuable tool for aerodynamic analysis and design.

HighlightS

  • Predicted streamlines, velocity magnitudes, and pressure coefficient distribution.
  • Showed a positive relationship with observable findings and conceptual ideas.
  • Model is restricted to non-lifting flows (only gives a general idea).

SKILLS

MATLABAerodynamicsSource Panel Method

ADDITIONAL CONTENTS

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Owen James Weisenberger

Aerospace Engineering Student at Syracuse University minoring in Physics

I'm an aerospace engineering student at Syracuse University with a strong foundation in structural analysis, aerodynamics, and computational methods. I have hands-on experience conducting wind tunnel experiments, designing optimized structures, and developing MATLAB solvers for complex engineering problems. Currently, I'm working on noise reduction in laser interferometry systems and designing reversible joints for DuPont's Corian® products, combining simulations, theoretical analysis, and experimental validation.