Aerodynamics and Fluid Mechanics Commons^™

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 …

Development Of A Liquid Propellant Rocket Engine With Integrated Water-Based Cooling Jacket, Mauricio Bautista, Jesus Cortes, Christian Lopez, Hugo Robles, Will Owens, Josh Sutton, Jayden Pace, Shelby Enlow

Create@State

This projects describes the development of a liquid rocket engine with a metal casted cooling jacket. We test the system and provide simulation data for the project.

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, …

Wind Tunnel Instrumentation And Testing, Nicholas Marek, Abraham Mezera, Laura Jin, Hayden Smith, Curtis Cook

Student Scholar Symposium

The Raymond B. Jones College of Engineering was contacted by an automotive engineering firm seeking to use the college’s wind tunnel for gathering data on the aerodynamic performance of a proprietary prototype automotive door. Specifically, the client requested the quantification of the drag coefficient of the model at extreme wind speeds. The drag coefficient, a dimensionless number that quantifies the resistance of a specific geometric shape to airflow, will be a valuable datapoint for the client’s design iteration. Due to the sensitive nature of their work, the client has wished to remain anonymous. RBJCOE professors tasked a senior design team …

Implementing A 5-Dimensional Tabulated Conditional Moment Closure Model With Scalar Dissipation Rate For Scramjet Combustion, Alp Tuztas, Scott Montgomery Martin, Carlos A. Velez

Discovery Day - Daytona Beach

The growing interest in Scramjets for achieving sustained hypersonic flight has given rise to numerous computational models to obtain solutions as close as possible to experimental data, assisting with making the design process of modern Scramjet’s with different propellants and cavity designs less costly. However, Scramjet engines pose significant challenges for computational modelling due to the need of accounting for large- and small-scale turbulences but also solving turbulence chemistry interactions in compressible flow regimes. A promising approach has been through using high-fidelity turbulence-combustion models which greatly assist with capturing detailed chemistry, account for small scale turbulence and the complex flow …

Production And Decay Of Sheared Turbulence In A Turbulence Box, Ankit Gautam

Student Research Symposium

Introduction

• Turbulence
• Irregular flow with eddies, swirls, and flow instabilities

Simulating Low Gravity Particle Dynamics, Ryan Lewis

Student Research Symposium

• Vibrating motors prevent particle arches from forming and clogging nozzle.
• A metal mesh under the nozzle creates an evenly dispersed stream.
• Nozzle is static dissipative to ensure particles have consistent path through the charging section.

Design Of A Two-Point Focused Laser Differential Interferometry System For The Missouri S&T Supersonicwind Tunnel, Joseph Villarreal, Davide Vigano

Miners Solving for Tomorrow Research Conference

No abstract provided.

Commercial Airliner Winglet Design Optimization – A Case Study, Anthony Gutierrez

Symposium of Student Scholars

The objective of this research is to determine the effect on aerodynamic performance due to changes of winglets design variables found of the Boeing 737-700 aircraft. The various winglet types studied in this research include the blended, canted, wingtip fence and split scimitar. The variables include height, sweep angle, taper ratio, and the inclination angle. These variables are altered in 5% increments from -15% to +15% of their original baseline values. Each altered winglet design only changes one variable at a time while keeping all other variables constant. The altered models are compared to the original by finding the aerodynamic …

Computational Analysis Of The Effects Of Scarfed Nozzle Variations On Jet Plumes, Andrew J. La Sorsa

ONU Student Research Colloquium

A computational fluid dynamics analysis investigating the variation of effects on nozzles with non-orthogonal exit planes, known as scarfing, was performed. The steady Reynolds-averaged Navier-Stokes model, coupled with the Spalart-Allmaras turbulence model, was used to simulate and compare plume development and characteristics using various scarfing geometries at variable inlet conditions. The jet plume cross-section is significantly affected for overexpanded conditions, while retaining the nozzle exit shape for underexpanded conditions, although slight peaks (bifurcation) do occur at the centerline. The same observations occur when slightly changing the angle of scarf. However, inverting the overall geometry of the diverging portion of the …

Effects Of Vortex Generator Placement On A Horizontal Axis Wind Turbine Blade, Dagan Sorensen

ONU Student Research Colloquium

Vortex generators are commonly used devices to control the flow over an airfoil or other surface. In this paper the effect of differing placements of vortex generators on a wind turbine airfoil, compared to an airfoil without vortex generators, were simulated using computational fluid dynamics(CFD). It was shown that, in some instances, the application of vortex generators effectively controlled the flow over the airfoil to increase the power produced by the wind turbine. According to the CFD results, the application of vortex generators at an angle increased the lift produced, as well as delaying the separation of the boundary layer.

Blade Optimization For Ground Level Low Speed Wind Turbines, Ryan Foster

Symposium of Student Scholars

Low speed wind turbines can provide inexpensive and clean energy in areas where large scale wind power generation is impractical. The purpose of this research is to explore factors that affect the efficiency of low speed wind turbine blades. The factors that were tested include angle of attack, angle of twist, chord length, average thickness, span, and taper ratio. The goal is to determine a combination of these variables to enable maximum power extraction from a low wind speed source. These blade parameters are optimized for the Southeastern region of the United States. NOAA weather data at ground level are …

Lifting Flow Over A Cylinder As A Lift System, Kyle Mello

Symposium of Student Scholars

The goal of this project is to conceptually design a lift system consisting of rotating cylinders that may improve certain flight characteristics when compared to conventional wings for a typical two passenger airplane. The functions of flaps, ailerons, lift to weight ratio and structural responses are considered. The cylindrical model is developed within CFD simulation software such that it generates the same lift produced by the wings of a Cessna 172 wings at cruising speed. Incompressible flow theoretical solutions are initially shown to compare favorably with the computational predictions for elementary cylindrical designs.

The rotating cylinder aircraft generates the same …

Perfromance Improvement Of High Bypass Turbofan Engine Through Optimization Of High-Pressure Compressor Blade – A Case Study, Vlad Mandzyuk

Symposium of Student Scholars

This research determines the relation between the High-Pressure Compressor (HPC) blade characteristics, compressor pressure ratio, and lift-to-drag ratio of a high bypass turbofan engine. Alterations in the HPC blades airfoil, span, chord, taper ratio, twist, aspect ratio, sweep, and angle of incidence are performed and their effect on the engine’s performance is observed. The metrics used to compare engine performance include thrust, specific thrust, exit velocity, fuel/air ratio, power, and efficiency. Parametric cycle analysis and computational fluid dynamics are performed to compare and validate findings. The goal of this study is to optimize the design of HPC to maximize the …

Supercritical Carbon Dioxide Based Heat Exchanger On The Martian, Sarah Guinn

Discovery Day - Prescott

The use of supercritical carbon dioxide (sCO2) in power cycles has been fairly new in the last decade. Due to this, there is a lack in research for both terrestrial and extraterrestrial applications. The purpose of this project is to utilize sCO2 as a working fluid and design and optimize a Brayton Cycle based heat exchanger on the Martian surface. Due to the lack of water on Mars, this research will provide a stronger analysis of planetary based drycooling processes in low atmospheric pressure and colder temperatures. We have been conducting an in-depth analysis of the heat exchanger by modeling …