Design Tools
Solidworks, CATIA V5, OpenFOAM, Ansys Workbench (Fluent,
Structural, Acoustics CFD, CFX), HyperMesh, Unity, FE Map (Nastran),
Ansys Mechanical APDL, FEHT, Tensor Flow, XFoil, XFLR5, X-Plane 11.
Programming Tools
MATLAB, Simulink, C++, HTML/CSS, JavaScript, C/C++, CNC
Programming, Visual Basic, Microsoft Office Suite.
Summary of Qualifications
• Accumulated over 150 hours of hands-on experience through
custom-developing CFD solvers in C++ as well as using CFD software
(ANSYS Fluent) to model and analyze complex 2D heat transfer and fluid
flow problems, including transient natural convection, laminar and
turbulent flow through structured, semi-structured, and multi-block
meshes.
• Demonstrated expertise in first-principles analyses and
aircraft performance methods, with working knowledge of FAR Part 23
and 25 airworthiness regulations.
• Gained 5+ years of experience using engineering tools including
MATLAB for numerical modeling and data analysis, SolidWorks and CATIA
V5 for 3D CAD design, and ANSYS Workbench for structural, thermal, and
flow simulations.
• Recognized team player with adaptive nature and proven ability
to multitask in a fast-paced environment showcased through academic
course work and Projects.
• Developed excellent interpersonal, time management, and
administrative skills through leading projects, managing tasks, and
executing assignments through extra-curricular activities (TMU Met
Rocketry, TMU Hyperloop) & Aerospace Capstone Project.
Engineering Resume
Skills &
Experties
Experties
Education
Master of Engineering - Aerospace Engineering | Toronto
Metropolitan University.
GPA: 4.26/4.33.
Relevant Courses: Computational Methods in Aerodynamic Analysis, High Speed Aerodynamics, Computational Fluid Dynamics and Heat Transfer, Computational Dynamics, Special Topics: Airfoils Design, Aircraft Turbine Engines, Aerospace Thermal Engineering, Aeroelasticity and Gas Dynamics, Vibrational Analysis, Aircraft Structural Design.
Bachelor of Engineering - Aerospace Engineering | Toronto Metropolitan University.
GPA: 3.5/4.33.
Graduated with Distinction.
GPA: 4.26/4.33.
Relevant Courses: Computational Methods in Aerodynamic Analysis, High Speed Aerodynamics, Computational Fluid Dynamics and Heat Transfer, Computational Dynamics, Special Topics: Airfoils Design, Aircraft Turbine Engines, Aerospace Thermal Engineering, Aeroelasticity and Gas Dynamics, Vibrational Analysis, Aircraft Structural Design.
Bachelor of Engineering - Aerospace Engineering | Toronto Metropolitan University.
GPA: 3.5/4.33.
Graduated with Distinction.
Sept. 2023 - June 2025
Sept. 2018 - June 2023
Academic &
Research Experience
Research Experience
Experimental CFD Research Assistant, Toronto Metropolitan
University.
• Performed transient CFD simulations to analyze natural convection heat transfer over a vertical hollow cylinder with circular fins, focusing on the effects of grid topology on solution accuracy and efficiency.
• Developed and analyzed structured, semi-structured, and multi-block meshes, and implemented a pressure-based solver with a RANS turbulence model in ANSYS Fluent.
• Conducted grid convergence studies and validated results against established benchmark data to ensure numerical accuracy.
• Determined that fine structured grids yielded the most accurate Nusselt number predictions but incurred higher computational costs; learned that non-linear grids enhanced boundary layer resolution but introduced mild numerical oscillations; demonstrated that multi-block grids provided a balanced trade-off between accuracy and computational performance.
• Performed transient CFD simulations to analyze natural convection heat transfer over a vertical hollow cylinder with circular fins, focusing on the effects of grid topology on solution accuracy and efficiency.
• Developed and analyzed structured, semi-structured, and multi-block meshes, and implemented a pressure-based solver with a RANS turbulence model in ANSYS Fluent.
• Conducted grid convergence studies and validated results against established benchmark data to ensure numerical accuracy.
• Determined that fine structured grids yielded the most accurate Nusselt number predictions but incurred higher computational costs; learned that non-linear grids enhanced boundary layer resolution but introduced mild numerical oscillations; demonstrated that multi-block grids provided a balanced trade-off between accuracy and computational performance.
Transonic Airfoil Design Research Assistant, Toronto
Metropolitan University.
• Designed a transonic airfoil by writing a custom MATLAB script to reduce lift degradation caused by normal shock waves at high tip Mach numbers in propeller-driven applications.
• Applied conformal mapping techniques (Joukowski and Karman-Trefftz transformations) to generate airfoil geometries with optimized camber and thickness distributions.
• Analyzed both compressible and incompressible flow behavior using Prandtl-Glauert corrections and thin airfoil theory to assess performance across subsonic and transonic regimes.
• Redesigned lower surface profiles to offset shock-induced lift losses while maintaining a manufacturable trailing edge geometry.
• Achieved full lift recovery post-shock, with the final design producing a compressible lift coefficient of 1.0842 at Mach 0.6353. Validated the final airfoil as a thin-profile geometry with optimal camber and angle of attack, confirming its aerodynamic efficiency for high-speed propeller use.
• Designed a transonic airfoil by writing a custom MATLAB script to reduce lift degradation caused by normal shock waves at high tip Mach numbers in propeller-driven applications.
• Applied conformal mapping techniques (Joukowski and Karman-Trefftz transformations) to generate airfoil geometries with optimized camber and thickness distributions.
• Analyzed both compressible and incompressible flow behavior using Prandtl-Glauert corrections and thin airfoil theory to assess performance across subsonic and transonic regimes.
• Redesigned lower surface profiles to offset shock-induced lift losses while maintaining a manufacturable trailing edge geometry.
• Achieved full lift recovery post-shock, with the final design producing a compressible lift coefficient of 1.0842 at Mach 0.6353. Validated the final airfoil as a thin-profile geometry with optimal camber and angle of attack, confirming its aerodynamic efficiency for high-speed propeller use.
FEA & Aircraft Structural Research Assistant, Toronto
Metropolitan University.
• Designed and modeled the internal wing structure of a Cessna 152, integrating ribs, spars, and stringers using SolidWorks for high-fidelity structural representation.
• Conducted Finite Element Analysis (FEA) in ANSYS Static Structural using both linear and quadratic tetrahedral elements to evaluate stress and deformation under aerodynamic and static loads.
• Simulated critical load cases, including wing loading, fuel weight distribution, and flight envelope extremes.
• Performed grid-independence studies with various mesh sizes and to ensure numerical reliability and eliminate mesh-sensitive errors. Calculated stress distributions and maximum deformation, verifying that all values remained within material limits.
• Confirmed that structural failure loads significantly exceeded operational loads, validating the wing design's robustness.
• Designed and modeled the internal wing structure of a Cessna 152, integrating ribs, spars, and stringers using SolidWorks for high-fidelity structural representation.
• Conducted Finite Element Analysis (FEA) in ANSYS Static Structural using both linear and quadratic tetrahedral elements to evaluate stress and deformation under aerodynamic and static loads.
• Simulated critical load cases, including wing loading, fuel weight distribution, and flight envelope extremes.
• Performed grid-independence studies with various mesh sizes and to ensure numerical reliability and eliminate mesh-sensitive errors. Calculated stress distributions and maximum deformation, verifying that all values remained within material limits.
• Confirmed that structural failure loads significantly exceeded operational loads, validating the wing design's robustness.
Computational Dynamics Research Assistant, Toronto Metropolitan
University.
• Designed and analyzed a dynamic parallel linkage mechanism to control the morphing winglet cant angle for improved aerodynamic performance and structural efficiency during flight.
• Applied inverse kinematics and wrote a custom script in MATLAB to compute joint positions, velocities, and accelerations, enabling precise actuator control.
• Performed dynamic motion analysis using the Euler-Newton Recursive method to calculate joint forces and actuator loads under varying flight conditions.
• Developed CAD models in SolidWorks for both static and dynamic configurations to visualize, simulate, and validate system behavior.
• Demonstrated linear actuator stroke-to-winglet rotation proportionality, achieving smooth motion with high stiffness and structural integrity. Validated system strength by computing joint forces and torques, thus, confirming its capability to withstand aerodynamic and payload-induced loads during the flight envelope.
• Designed and analyzed a dynamic parallel linkage mechanism to control the morphing winglet cant angle for improved aerodynamic performance and structural efficiency during flight.
• Applied inverse kinematics and wrote a custom script in MATLAB to compute joint positions, velocities, and accelerations, enabling precise actuator control.
• Performed dynamic motion analysis using the Euler-Newton Recursive method to calculate joint forces and actuator loads under varying flight conditions.
• Developed CAD models in SolidWorks for both static and dynamic configurations to visualize, simulate, and validate system behavior.
• Demonstrated linear actuator stroke-to-winglet rotation proportionality, achieving smooth motion with high stiffness and structural integrity. Validated system strength by computing joint forces and torques, thus, confirming its capability to withstand aerodynamic and payload-induced loads during the flight envelope.
Sept. 2024 - Dec. 2024
Sept. 2024 - Dec. 2024
May. 2024 - Aug. 2024
Jan. 2024 - April 2024