Research & Projects

Project 1

Linearization of Mid-Fidelity Aerodynamic Solver

The main objective was to create an aerodynamic solver that balances accuracy and efficiency for simulation-based design and control. Specific goals included implementing and validating the coupled VVPM–panel framework, deriving analytical linearizations for state-space representation and real-time use, and embedding the solver into flight simulation environments to enhance aerodynamic prediction for stability, control, and performance studies.

Objectives

Results

The solver demonstrated the ability to accurately reproduce key aerodynamic phenomena for both rotorcraft and fixed-wing cases, with strong agreement against experimental and high-fidelity data. Analytical linearization reduced computational cost significantly, achieving real-time capability without loss of accuracy. Integration into flight simulation environments improved control prediction and stability analysis, providing a computational tool that bridges the gap between high-fidelity CFD and low-order engineering models.

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Project 2

Aerodynamic Design of Box-Wing Rotorcraft for VFS Design Competition

The project focused on the aerodynamic design of Wyvern, a hydrogen-powered electric compound rotorcraft developed for the 42nd Annual VFS Student Design Competition. The concept featured an innovative box-wing configuration, an aerodynamically efficient fuselage, and low-drag landing gear structurally integrated with the airframe to meet long-endurance loiter requirements with zero emissions.

Objectives

The objective was to design a rotorcraft that combined aerodynamic efficiency with environmental sustainability. This included assessing the feasibility of a box-wing configuration, optimizing the fuselage for drag reduction and structural efficiency, and designing low-drag landing gear while ensuring smooth integration with the overall airframe. The design also aimed to achieve over four hours of loiter using hydrogen-electric propulsion.

Results

Our design won the 1st place. The final design delivered a lift-to-drag ratio above 9.5, enabling more than 4.5 hours of loiter on hydrogen-electric power. The box-wing configuration enhanced aerodynamic efficiency and structural performance, while the optimized fuselage and integrated landing gear reduced drag and supported payload and fuel cell requirements. The result was a novel rotorcraft concept that successfully balanced performance, sustainability, and practicality for the competition.

Project 3

Numerical Investigation for a 2-D Moving Flapping Wing

This project developed a finite element solver to simulate incompressible viscous flow over a two-dimensional flapping wing. The solver incorporated a customized interface capturing scheme, a simplified aerodynamic force module, and rigid-body coupling to model wing kinematics. Validation against benchmark data was followed by a parametric study on the influence of flapping parameters.

Objectives

The aim was to build a computational framework for simulating flapping-wing aerodynamics. Key objectives included implementing an incompressible viscous flow solver, integrating rigid-body motion equations, validating the model against benchmark cases, and analyzing how variations in flapping amplitude, frequency, and phase affect trajectory and aerodynamic efficiency.

Results

The solver accurately reproduced fluid–structure interactions of a flapping wing and showed strong agreement with benchmark data. The parametric study identified clear trends in trajectory stability, lift generation, and efficiency, offering insights into the aerodynamic mechanisms of bio-inspired flight and demonstrating the solver’s value for studying unsteady aerodynamics.

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Project 4

Design and Manufacturing of a Trailing Edge Morphing Wing

This project explored the design and analysis of a trailing edge morphing wing actuated by Shape Memory Alloy (SMA) wires. The concept replaced traditional hinged control surfaces with a smooth, flexible trailing edge to reduce drag and eliminate aerodynamic gaps. Numerical simulations were performed in ANSYS Fluent with dynamic meshing to capture the interaction between structural deformation and unsteady aerodynamic loading.

Objectives

The objective was to evaluate the feasibility and aerodynamic benefits of trailing edge morphing. This included designing an SMA-based actuation system, developing a flexible trailing edge structure, and assessing aerodynamic performance improvements through numerical simulations. The project also sought to examine the coupling between morphing deformation and unsteady aerodynamic forces.

Results

The study demonstrated that SMA actuation enables smooth trailing edge deflections, avoiding the drag penalties of conventional control surfaces. Simulations showed reduced drag and higher lift-to-drag ratios compared to baseline designs. Dynamic meshing effectively captured fluid–structure coupling, confirming morphing wings as a promising alternative for improved aerodynamic efficiency and flow control.

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