Aerodynamics and Fluid Mechanics Commons^™

Modeling Of Supersonic Wave And Shock Propagation Using The Lattice Boltzmann Method, Timothy P. Schroeder

Beyond: Undergraduate Research Journal

The lattice Boltzmann method (LBM) has emerged as a mesoscopic alternative to traditional Navier-Stokes solvers for modeling fluid dynamics offering advantages in computational efficiency, parallelization, and handling of complex boundaries. Despite these strengths, accurately reproducing compressible, shock-driven phenomena remains challenging. This study investigates the performance of LBM in simulating the Sod shock tube problem, a classical benchmark for compressible flow-using both single and double distribution function formulations across one- and two-dimensional lattice stencils. A MATLAB-based solver was developed to model the flow under isothermal conditions and compared to the analytical solution using the L2 norm error. The one-dimensional models achieved …

Flight Testing And System Identification Of An Experimental Cessna 182, Mariano Chavez Rangel

Discovery Day - Daytona Beach

Flight testing and system identification are essential for accurately characterizing aircraft dynamics and supporting the development of reliable flight control systems. This work presents the use of an experimental Cessna 182 as a full-scale platform for flight testing and system identification, conducted by the Eagle Flight Research Center. The objective is to generate high-fidelity flight data to estimate aerodynamic and dynamic coefficients and establish a baseline model for comparison with a sub-scale aircraft incorporating Integrated High-Lift Propulsor (IHLP) technology. The experimental aircraft is equipped with a comprehensive onboard instrumentation suite designed to capture synchronized measurements of air data, aircraft motion, …

Experimental Cyber-Physical Platform For Aircraft Dynamic Response Across Subsonic To Hypersonic Regimes, Michael Poinsett, Gabriel Martinez

Discovery Day - Daytona Beach

Understanding how aircraft behavior changes across different flight regimes is essential for modern aerospace design, yet it is often limited to theoretical or purely computational analysis. This project aims to provide an experimental approach to visualize and study these dynamic changes in a more intuitive and practical way. The primary objective is to develop an experimental cyber-physical platform capable of representing aircraft dynamic response across a wide range of flight conditions, from subsonic to hypersonic regimes. The system is designed to (1) analyze how key dynamic parameters vary with changing conditions and (2) provide a physical representation of these effects …

Flightless Eagles And The Redbull Flugtag Experience: How We Built A Manned Low-Speed Glider Out Of Foam And Cardboard, Peter Ulrich, Vansh Varak, Tanay Agarwal, Stanlie Cerda-Cruz, Madison Warner, Rohan Patel

Discovery Day - Daytona Beach

This project documents the iterative engineering, design, and construction efforts behind 2 20-foot human-carrying gliders developed by a team of Embry-Riddle students for the Red Bull Flugtag competition. The challenge required balancing aerodynamic performance, structural efficiency, and themed creativity while adhering to strict dimensional and weight limits. Over two consecutive years, the team used both conceptual and computational methods, ranging from initial sketches and precedent research to software-based aerodynamic modeling, subscale testing, and full-scale fabrication, to optimize glide performance in a low-speed, low Reynolds number flight regime. The work emphasized the value of interdisciplinary collaboration, communication, and hands-on engineering judgment …

Preliminary Jetpack Design For Air, Space, And Sea Applications, Andrew Thummel

Discovery Day - Daytona Beach

This course work is intended as an exploratory engineering and design program dedicated to the building and testing of an underwater jetpack design, using dynamic similarity principles to extrapolate how tested results and performance in an underwater environment transition to airborne or zero gravity testing. By testing underwater, it is estimated that the design will attain a Reynolds number in the range of 8 to 10 million, creating novel qualitative research on how a blended wing body jetpack design built at human scale performs and handles in extremely turbulent and high Reynolds number flows.

Project Chimaera: Development Of A Tessellated Tetrahedral Truss Structure For Adaptive Multi-Regime Morphing Wing Technology, Evan Meyer, Eric Rodarte, Maximo Failla, Joshua Shuster, Jackson G. Schuler

Discovery Day - Daytona Beach

Project Chimaera: Physical Assembly of tessellated tetrahedral wing for Multi-Regime Flight. Modern Aircrafts lose aerodynamic efficiency because they are primarily made utilizing fixed wings which are designed for a single optimal flight condition. This forces an aircraft’s performance to become compromised across various speed maneuvers and flight regimes. Project Chimaera addresses this limitation through the development of a morphing wing capable of dynamically changing its geometry extensively during flight to allow an aircraft to travel between subsonic, supersonic, and hypersonic speeds. Whereas traditional wings rely on wing flaps and other flight controls; Project Chimaera addresses the limitation of flight controls …

Trim Characteristics And Its Importance, Daviel Peralta

Discovery Day - Daytona Beach

This project will go into the characteristics that lead to the concept of “Trim adjustment” in aircraft by modeling and demonstrating physical principles and mathematical concepts under ideal conditions. We will derive an equation from the basic physical principles of torque and lift to demonstrate how the trim is adjusted in steady, constant velocity flow for the sake of the pilot’s ease of control and to induce stability in flight. These adjustments are considered differently with different types of aircraft; as such, we will be focusing on mono-fixed-winged aircraft with one engine and conventional helicopter designs. Both flying devices will …

Turbine Aerodynamics And Performance Characterization, Anuranan Bharadwaj, Kalkamanali Satvaldy, Vincent Shi

Discovery Day - Daytona Beach

This research presents an integrated study combining computational modeling and experimental validation to enhance the design and performance characterization of small-scale turbine systems. The theoretical component focuses on developing an object-oriented Python code for the preliminary design and performance prediction of radial turbines, capable of generating velocity triangles, thermodynamic properties, and geometric parameters from user-defined inputs. The tool employs Whitfield-based correlations and fundamental gas-dynamic relations to estimate exit flow parameters, work ratio, and efficiency, offering flexibility for expansion into geometry export and CAD integration.   Complementing the computational model, the experimental component aims to improve the aerodynamic testing capabilities of the …

Generalized Cloud-Based Compressible Aerodynamics Calculator And Simulation Web App, Massimo Mansueto, Liam Griesacker, Andres Torres-Figueroa

Discovery Day - Daytona Beach

The Generalized Cloud-Based Compressible Aerodynamics Calculator and Simulation Web App focuses on the development of a tool to support the analysis, visualization, and teaching of compressible aerodynamics. In the case of most undergraduate aerospace engineering courses, students rely on static equations, charts, and manual calculations, which can make it difficult to conceptualize complex flow phenomena such as shock waves, expansion fans, and nozzle flow. The purpose of this project is to create an accessible platform that integrates a compressible flow calculator, nozzle sizing tool, and interactive simulations into a single educational resource. The application is implemented using modern web development …

Extending The Essentially Entropic Lattice Boltzmann Method To Three-Dimensional Turbulent Flows, Michael Derderian

Discovery Day - Daytona Beach

The Entropic Lattice Boltzmann Method (EELBM) has demonstrated strong numerical stability and accuracy for two-dimensional simulations, particularly at higher resolutions where the entropic formulation introduces only minimal stabilizing turbulent viscosity and eventually converges to the Lattice Bhatnagar–Gross–Krook (LBGK) formulation. This built-in stabilization can be interpreted as an implicit large-eddy simulation (LES) model, allowing EELBM to capture complex turbulent behavior without requiring explicit subgrid-scale closures. While these advantages have been thoroughly validated in 2D, understanding how the entropic constraint regulates dissipation in three dimensions is essential for assessing EELBM’s suitability for practical, turbulence-dominated applications. This work focuses on the development and …

Modeling The Effect Of Damping On Mechanical Vibrations In An Aircraft Wing, Daniel Ingleton, Ethan Burrell, Noah Evans

Discovery Day - Daytona Beach

Aircraft wings experience vibrations during flight due to aerodynamic forces, turbulence, engine effects, and the flexibility of the structure itself. If these vibrations are not properly controlled, they can affect the wing’s performance, structural life, and overall aircraft safety. This research project focuses on modeling how damping reduces mechanical vibrations in an airplane wing. To make the problem manageable, the wing will be represented as a simplified cantilever beam. The project will examine how damping, stiffness, and mass influence the wing’s vibration response over time. Using mathematical equations of motion and simulation tools such as MATLAB or ANSYS, the study …

Simulation-Based Analysis Of Aeroelastic Flutter Using A 2-Dof Mass–Spring–Damper Model, Jamie Shore, Jose Murphy, Emily Brown, Leia Vargas Ii, Carl Pellegrino

Discovery Day - Daytona Beach

This research project focuses on utilizing a mass-spring dampening system to analyze wing flutter. Given that wing flutter is an instability caused by elastic and inertial forces, these create increasing oscillations that lead to structural failure. Our group will create a simulator developed in MATLAB to analyze data on how different variables such as angle of attack, aspect ratio and wind speed influence the flutter. The simulation will help us to determine how flutter is affected by mass, structural stiffness, and the damping coefficient on several materials. These materials include aluminum 6061, birch wood, steel 36, and tungsten. The goal …

Navier Stokes Pressure Drop Derivation, Brayden Benedetti, Gedaliah Dimbert, Jaden Turobiner

Discovery Day - Daytona Beach

Accurate prediction of pressure losses in propellant and fluid feed systems is essential for reliable design and operation of aerospace and industrial flow networks. This project presents a systematic derivation of a practical pressure drop calculator for a feed system using isopropyl alcohol, beginning from the fundamental conservation laws and culminating in an engineering-level computational model. Starting with the differential form of the Navier–Stokes equations for incompressible flow, the governing equations are simplified through a series of physically justified assumptions, including steady-state flow, negligible body forces, and fully developed internal flow within circular piping. The resulting momentum balance is reduced …

Application Of Navier Stokes In Cfd, Hayden Kerkhoff, Gavin Palmer, Garret Seckinger

Discovery Day - Daytona Beach

This project investigates the use of 2-Dimensional Computational Fluid Dynamics (CFD) to analyze aerodynamic behavior, then compare data with the numerical solution of the Navier–Stokes equations run by MATLAB. By leveraging open‑source and possible industry CFD platforms—including OpenFOAM and commercial solvers such as ANSYS Fluent and Inventor Professional—the study evaluates how computational methods simulate, optimize, and predict key aerodynamic quantities such as lift, drag, stall angle, and Reynolds number.   The project focuses on modeling an airflow over specific parameters, such as different angles of attacks and ISA Atmospheric Conditions. Parametric variations in density, angle of attack, chord length, and temperature …

Cavitation In Pumps And Propellers: Causes, Effects, Prevention, And Future Trends, Gillian Negron Burgos, Olivia Wilson

Discovery Day - Daytona Beach

In this research, we will explore cavitation in pumps and propellers, including its causes, effects on system performance, prevention methods, and future engineering solutions. Cavitation occurs when the local pressure of a flowing liquid drops below its vapor pressure, forming vapor-filled bubbles that collapse and damage mechanical components. Disciplines such as fluid mechanics, thermodynamics, and materials science contribute to understanding and mitigating cavitation in fluid machinery.   When vapor bubbles collapse near metal surfaces, they generate localized shock waves that cause pitting, erosion, vibration, and noise. These effects reduce efficiency, increase maintenance requirements, and shorten the lifespan of rotating machinery used …

Numerical Modeling Of Badminton Shuttlecock Trajectories, Lola G. Torres, Cassandra Pumphrey, Jadyn Peterson, Domenic Barsotti

Discovery Day - Daytona Beach

The Trajectory of a badminton Shuttlecock can vary significantly when compared to a classic projectile motion, primarily due to aerodynamic drag. This project aims to model the flight of the shuttlecock using Newton's second law for gravitational and drag related forces, resulting in a nonlinear system of a first order differential equation. The given parameters include the shuttlecock mass, cross-sectional area, air density, as well as the drag coefficient, determining the overall magnitude of the drag force. The resulting initial value problem is solved numerically using a multitude of Runge_Kutta methods to compare the accuracy and stability across different computational …

Motion With Air Resistance, Gauge Mccain, Jacob Bealefeld, Francesca Wise

Discovery Day - Daytona Beach

The motion of objects moving through air is influenced not only by gravity but also by air resistance, which affects the speed and acceleration of the object over time. This project examines the motion of a falling object by modeling it with an ordinary differential equation that accounts for both gravitational force and a resistive drag force proportional to velocity. Using Newton’s Second Law, a first-order differential equation is derived to describe how the velocity of the object changes as it falls. The solution of this equation demonstrates how the velocity increases initially and gradually approaches a constant value known …

Powered Parachute Vehicle For Crew Transportation On Mars, Louis J. Spier

Beyond: Undergraduate Research Journal

To support possible future human presence on Mars where bases are likely to be spread apart, aerial vehicles could be used to transport crew and cargo between them. Designing and operating such a vehicle is very challenging because of the low atmospheric density on Mars compared to Earth, the logistics involved with transporting it to Mars, and the infrastructure necessary to operate it. This study discusses the problems involved with designing, building, and operating fixed-wing and powered parachute aircraft on Mars and presents a concept involving a powered parachute vehicle utilizing an inflatable parachute wing that can be packed together …

Effect Of Solid Particle Size And Density On Incipient Motion In A Turbulent Boundary Layer, Robert Bryan

Doctoral Dissertations and Master's Theses

Wind-blown sand and other instances of solid particles mobilized and suspended in gaseous turbulent boundary layers (TBLs) are seen in a wide variety of engineering contexts. An experimental framework was developed to study the incipient particle motion driven by external forcing within a turbulent boundary layer, which is provided by an airfoil section oscillating in the free-steam flow, resulting in a periodic disturbance in the near-wall region through production of synthetic large-scale structures at a fixed frequency. The incoming unsteady carrier-phase eddies were measured with a hot-film sensor upstream of a particle bed, and the particle motion was captured by …

Experimental-Motion-Driven Cfd Investigation Of Slosh Dynamics In Propellant Tanks Of Spacecraft And Launch Vehicles, Priyanshu Savaliya

Doctoral Dissertations and Master's Theses

Liquid sloshing in partially filled propellant tanks can generate transient forces and moments that affect spacecraft and launch vehicle stability, guidance, and control. This research develops a one-way experimental-to-Computational Fluid Dynamics (CFD) integration framework to investigate free-surface slosh behavior under realistic excitation conditions.

The overarching goal of this thesis is to develop and evaluate a one-way experimental-motion-driven computational framework for predicting liquid slosh response in a partially filled cylindrical tank. Rather than relying on idealized sinusoidal inputs, this work uses experimentally measured actuator-feedback motion as the prescribed excitation for high-fidelity CFD. The central objective is to establish the experimental and …

Optimal Integrated Cfd-Gnc Model For Drag-Based Reentry Dynamics, Sebastian Lopez

Doctoral Dissertations and Master's Theses

This research focuses on optimizing the control of a drag-maneuvering, Starship-class re-entry vehicle by closely integrating high-fidelity aerodynamic data derived from Computational Fluid Dynamics (CFD) simulations, specifically using StarCCM+. The aerodynamic models, tailored to the unique geometry of a drag-maneuvering body, are seamlessly incorporated into a guidance, navigation, and control (GNC) framework. This integration enables closed-loop CFD simulations with real-time control feedback, allowing for direct analysis and optimization of vehicle stability, trajectory, and control demands throughout the re-entry process.

Building upon the work of Gaglio and Bevilacqua, this advanced CFD-GNC model introduces high-order aerodynamic effects, such as aerodynamic moments and …

Numerical Investigation Of Shock-Induced Deformation Of Bubble-Laden Droplets, Juan Roldan

Doctoral Dissertations and Master's Theses

Rain impact can be a source of surface erosion on hypersonic vehicles, and the severity of each impact depends on droplet velocity, mass, and final shape, all of which are set by how the droplet breaks up under shock loading. Real droplets are expected to carry entrained non-condensable gas (NCG) nuclei from their formation. This dissertation investigates whether the purely mechanical, pressure-driven response of these nuclei, independent of vaporization, is large enough to measurably alter the internal pressure field and early deformation of a shock-loaded droplet.

The droplet and surrounding gas are modeled with a compressible, diffuse-interface, axisymmetric Eulerian framework …

Aerodynamic And Acoustic Modeling For Evtol Rotor Noise Prediction, Daniella Bezuidenhout, Anastasios S. Lyrintzis, Vladimir V. Golubev

Doctoral Dissertations and Master's Theses

This thesis presents the development and validation of a methodology for predicting total acoustic emissions from a one-fifth scale electric vertical takeoff and landing (eVTOL) rotor in both hover and edgewise flight conditions. The approach couples sectional two-dimensional Reynolds-Averaged Navier-Stokes (2D-RANS) airfoil simulations with rotor loading predictions from the Comprehensive Hierarchical Aeromechanics Rotorcraft Model (CHARM), tonal noise calculations using the acoustic solver PSU-WOPWOP, and broadband noise predictions from the UCD-QuietFly framework. Boundary-layer inputs traditionally obtained from the viscous-inviscid solver, XFOIL, were replaced with higher-fidelity 2D-RANS results from OpenFOAM to better capture low-Reynolds-number flow physics, including laminar-turbulent transition and laminar separation …

Contributions To Ship-Airwake-Rotor Coupling Characterization Using Controlled Forcing, Guillermo Mazzilli

Doctoral Dissertations and Master's Theses

Shipboard helicopter operations occur within a highly unsteady environment referred to as the dynamic interface (DI), encompassing the coupled effects of the ship airwake, rotor wake, flight dynamics, and pilot response. A central aspect of the DI is the aerodynamic interaction between the ship airwake and the rotor wake, which degrades handling qualities and increases pilot workload, yet the underlying mechanisms governing ship-rotor coupling remain insufficiently understood. The ship-rotor aerodynamic coupling was examined using two canonical ship geometries, the NATO-GD and SFS2, together with a controlled experimental framework, the airflow-and-blade-frequency (ABF) system, which independently varied wake momentum flux and unsteady …

Numerical Study Of Nutrient Mixing In Trabecular Bone In Microgravity, Disuse And Normogravity, Sagar Gharti

Doctoral Dissertations and Master's Theses

Mechanical loading is known to regulate bone remodeling by driving interstitial fluid flow which stimulates cells and drives nutrient transport within the trabecular network. In microgravity, the absence of mechanical stimulation or loading suppresses convective flow processes, causing diffusion-driven nutrient mixing and renewal, and accelerated bone loss. This thesis investigates how oscillation frequency and trabecular bone density jointly control nutrient mixing and wall shear stress within trabecular cavities.

A computational fluid dynamics (CFD) framework is developed in STAR-CCM+ using a soft-cap oscillation model that mimics cyclic compression. Three idealized trabecular morphologies are simulated across different frequencies to represent microgravity or …

Instrumentation And Control Of A Novel Device To Simulate A Hypersonic Environment, Andrew Marcello

Doctoral Dissertations and Master's Theses

The hypersonic flow regime poses several challenges regarding the design of hypersonic vehicles. Among them is the massive energy and economic expense associated with ground- testing evaluation of material responses within this extreme environment. In order to provide a low-cost, rapid option for preliminary material analysis within hypersonic applications, a novel device is under production to replicate this environment on the surface of these materials. This device has been designed to work in conjunction with Argonne National Laboratory (ANL) Advanced Photo Source (APS) synchrotron, to allow for in-situ characterization of ablation and oxidation on the sample surface.

To achieve this, …

Numerical Investigation Of Rotor-Gust Acoustic Interactions Using The Overflow Cfd Solver, Jordan Mills

Doctoral Dissertations and Master's Theses

The rapid expansion of Urban Air Mobility (UAM) necessitates high-fidelity modeling to predict and mitigate the noise signatures of electric vertical take-off and landing (eVTOL) aircraft within dense urban landscapes. A critical unknown in community-noise certification is the aeroacoustic response of rotors to unsteady inflow conditions. This research addresses this gap by investigating the aerodynamic and acoustic behavior of a representative rotor subjected to time-harmonic inflow disturbances. By establishing a robust numerical framework, this thesis quantifies the relationship between periodic atmospheric gusts and their impact on rotor performance, unsteady blade loading, and subsequent sound radiation. The research consists of a …

Effect Of Nozzle Pressure Ratio On Thrust And Flow Behavior In A Supersonic De Laval Nozzle, Esha Jain

Doctoral Dissertations and Master's Theses

Supersonic nozzles operate across a range of flow regimes. While an ideally expanded condition yields optimal thrust, practical propulsion systems rarely operate at this design point due to variations in altitude and engine operating conditions. As a result, nozzles frequently operate in off-design conditions. In overexpanded regime, where the exit pressure is lower than the ambient pressure, shock-induced separation may occur within the divergent section of the nozzle, potentially degrading nozzle performance. Understanding the aerodynamic behavior of nozzles operating under off-design conditions is therefore important for improving propulsion system performance and stability. In particular, direct thrust measurements provide a key …

Quantification Of The Depth-Of-Field In A Self-Aligned Focusing Schlieren System, Alexander Ephraim

Doctoral Dissertations and Master's Theses

This thesis investigates self-aligned focusing schlieren (SAFS) as a step toward future volumetric and quantitative measurements of three-dimensional compressible flows. Conventional schlieren imaging provides valuable visualization of density gradients, but it records only a line-of-sight projection and therefore does not directly resolve the spatial distribution of structures through the depth of the flowfield. SAFS addresses part of this limitation by introducing depth sensitivity, but its depth response has not been well characterized quantitatively. To help lay the foundation for future volumetric and quantitative SAFS methods, this work addresses two related problems. First, calibrated quantitative schlieren imaging is applied to an …

Computational Study Of Slosh Dynamics And Active Slosh Damping In Spacecraft Propellant Tanks Equipped With A Magneto Active Propellant Management Device, Priyanshu Savaliya

Student Research Symposium (SRS)

The management of liquid propellant in microgravity remains one of the longest-standing issues in spacecraft design. Traditional passive damping techniques using baffles or diaphragms tend to add structural mass and complexity. The current study proposes a novel active slosh damping device which dynamically adjusts the rheology of the damper fluid using electromagnets, simulated in ANSYS Fluent, to actively manage and dampen slosh in an oscillatory excited cylindrical propellant tank. The electromagnetic fields are modulated through a User-Defined Function (UDF) that responds to force feedback simulated in real time via virtual load cells. In Fluent, the interface dynamics of xenon, fuel, …