Aerospace engineers design high-performance systems, including aircraft, spacecraft, satellites and missiles. They have an understanding of aerodynamics, flight mechanics, structures and propulsion. Our graduates work in analysis/design and research/development for local, national and international companies and organizations.
2025 Senior Design Projects
MEMBERS: Erik Andersen , Lucas Baker, Derek Eitzmann, Tracey Hill , Zach Silvis
ADVISOR: Dr. Jielong Cai
SPONSOR: Boeing
Aces Aerospace has developed a half-scale model for a cutting-edge unmanned short takeoff and landing (STOL) aircraft that is designed to address the logistical challenge of transporting scientific samples from both remote and urban environments. Our team aims to solve this issue by providing an aircraft engineered with long-range, high payload capacity, and a minimal runway requirement. This enables our aircraft to serve several industries such as medical research, environmental monitoring, and emergency response. Aces Aerospace interviewed a research professor with WSU Geology, a strategic partnership manager at NASA, and a special agent with the FBI. Based on these interviews, a list of real-world payloads could include water samples, geological samples, forensic evidence, and medical specimens. Our aircraft can provide faster access to critical data by having equipment on board that can begin sample analysis, producing results such as identification of bacterial pathogens in water, composition of rock samples, blood type from a crime scene sample, or viral infection identification on a test sample. An additional benefit of our aircraft is its compact frame, roughly the width of an SUV, allowing the aircraft to maneuver in tight areas and land on single-lane roads within 30ft. Furthermore, the unmanned small-scale design allows the customer to receive the same benefits as a full-scale aircraft at a much lower purchase price with lower operational costs. In summary, the Aces Aerolink provides the perfect solution for scientific sample transportation by providing fast access to critical data while being versatile enough to tackle any terrain.
MEMBERS: Brody Hendrich, Nicholas Janzen, Radeef Karim, Connor O'Neill, John Cummings
ADVISOR: Dr. Jielong Cai
SPONSOR: Boeing
Delivering emergency medical supplies promptly during high traffic or natural disasters becomes almost impossible. Patients and EMS personnel require lifesaving interventions as soon as possible. Mach Street Boys aims to deliver these crucial supplies to those in need via Urban Air Mobility, known as Aerial Emergency Medical Suppliers (AEMS). Mach Street Boys is committed to easy accessibility and ensures that deliveries reach all destinations swiftly. AEMS will be a full-scale product capable of holding a payload that will ultimately be delivered to the desired location. What makes AEMS unique is its ability to maneuver urban environments more efficiently than other transportation aircraft required to unload at specific locations. The AEMS aircraft can take off and land from a shorter runway, making it ideal to fly in and out of tight spaces to deliver essential supplies.
MEMBERS: Treyton Blecke, Luke Cotter, Diego Fuentealba, Aiden Holt, Kaishi Kawakami
ADVISOR: Dr. Jielong Cai
SPONSOR: Boeing
An often-overlooked part of disaster relief is the need for power and internet service. A wide array of natural disasters can cause power and Wi-Fi outages. Disasters such as hurricanes, earthquakes, tornadoes, snowstorms, sandstorms, wildfires, and even heat waves and extreme cold can over-stress power grids. Many companies and humanitarian groups focus on the delivery of medical equipment, food, water, and other humanitarian aid. While such aide is critical, it does not help important infrastructure like hospitals, water plants, and waste processing plants maintain power. Additionally, large swaths of the population are often left without the power needed to run their refrigerators, heating and cooling units, medical equipment, and other power-dependent equipment. They may be left without internet connectivity, leaving them unable to receive important updates from officials, call for help, or check on family members and friends. Therefore, an aircraft that can provide power and internet connectivity equipment for urban areas affected by natural disasters, such as generators, gas, oil, batteries, satellite internet router-modems, solar panels, and battery powered/crank radios, has been designed. The aircraft utilizes short take-off and landing capabilities to perform maneuvers and reach areas in critical conditions that other vehicles/aircraft are unable to reach. With this ability, this plane can support urban areas in need.
MEMBERS: Francisco Murillo, Lanie Mott, Christopher Montford, Allinsipas Montoya
ADVISOR: Dr. Jielong Cai
SPONSOR: Boeing
Meadowlark Views is a STOL UAV that will conduct air tourism routes in picturesque skyline cities. The purpose of this aircraft will be to carry a customer’s phone for them to experience the city through their camera. To achieve this STOL mission, Meadowlark Views will take off from a short 16-foot elevated runway, fly around the Heskett Center second-floor gym, land on a 50-foot runway, fly again, and then land on the 16-foot elevated runway. To take off from the short 16-foot runway, the team will utilize flaps that provide additional lift and a three-bladed 11x7E propeller to reach take-off speed within the runway length. During flight time, the aircraft will rely on its US-35B airfoil to generate enough lift to fly at a cruise speed of about 35 ft/s. Additionally, Meadowlark Views will use its aileron, rudder, and elevator control surfaces to maneuver around the tight corners of the Heskett gym which will simulate the small enclosed spaces of an urban region. Finally, to land, the team will use the flaps again to act like spoilers to provide more drag for the plane to slow down to a stop within 16 feet. The completion of this mission will result in an enjoyable flight experience for the customers to experience through their phones.
MEMBERS: Jordan Glover, Caleb McDaniel, Marion Jackson, Celestino Almeida
ADVISOR: Dr. Jielong Cai
Our mission is to assist the ariel surveillance sector by providing an ariel platform that is cost effective, easy to manufacture, and easy to integrate into their daily operations.
The design is to emulate a surveillance operation in which the aircraft will takeoff, perform an aerobatic maneuver, land for payload pickup, and then return to the maneuvering phase before final landing.
MEMBER: Darsh Choksi, Kody Sudol, Laura Santos, Phanindar Pokala, Tyler Shuford
ADVISOR: Dr. Jielong Cai
SPONSOR: Boeing
Each year, 24 percent of weather-related vehicle accidents occur on icy, slushy, or snowy conditions, accounting for over 116,800 injuries in the United States [1]. Current ground road maintenance is time consuming and dangerous. By taking advantage of the growing Urban Air Mobility (UAM) market, STARFLEET introduces the DE-ICER 1 aircraft as a key solution to address winter transportation challenges. The De-Icer 1 is an eco-friendly electric aircraft made with composite materials; designed for precise aerial delivery of de-icing agents onto bridges. With its short takeoff and landing (STOL) capabilities, it may be deployed from the heart of a city- such as a rooftop, reaching critical areas faster than snow trucks. With this solution, drivers will not have to face the dangerous conditions that bridges present in icy/snowy conditions. State governments may benefit from reducing salt overuse which harms the environment, minimizing road closures and improving efficiency of de-icing procedures within cities. The De-Icer 1 offers a simple design so that design changes may easily be made to fit various use cases, enabling off-season functionalities-all while being eco-friendly and cost efficient. This airplane has the power to transform city-wide road safety as we know it, reducing accidents, saving lives and minimizing its carbon footprint.
[1] National Weather Service.
MEMBERS: Jacob Mohlman, Jance Wehkamp, Oscar Fernandez, Logan Janes, Antonio Rojas
ADVISOR: Dr. Suresh Keshavanarayana
This project focuses on the design, construction, testing, and successful flight of a custom built aircraft. A primary goal was to integrate the major areas of aerospace engineering principles (Aerodynamics, Flight Dynamics and stability, Structural Analysis, and Propulsion systems) to develop not only a functional aircraft, but one designed to a specific goal to meet mission criteria. The team started with a conceptual design followed with iterations of detailed simulations, analyses, and eventually a detailed, finalized design. After the construction of the aircraft, the team conducted a series of structural and wind tunnel testing to verify or modify certain characteristics impeding stability about the aircraft. The team then took to the skies to showcase their valuable work and dedication to the aerospace field of study. This project provided invaluable experience in applying a growth of knowledge to a practical, real world, engineering setting. It used teamwork, patience, problem solving, and innovation to overcome the challenges of aircraft design and testing.
MEMBERS: Nicholas Inzerillo, Andres Erives, Nathan Atkison, Jospeh Melero
ADVISOR: Dr. Jielong Cai
Short takeoff and landing aircraft (STOL) can fly a wide variety of missions in urban
settings. One mission that stood out was the transportation of medical items between
hospitals in dense urban areas. It was decided to build a STOL aircraft that is capable
of takeoff from a hospital roof with fragile pharmaceutical supplies. These supplies
would be air dropped onto the roof of another hospital. The glass eggs being transported
mimic the fragile pharmaceutical supplies the aircraft would need to transport in
the real applications.
Currently, hospitals use ground vehicles to transport pharmaceutical supplies between
hospitals. While these vehicles can get the job done, they are prone to delays due
to road conditions such as traffic and construction making them less ideal for patients
in critical condition. Aircraft can completely bypass road conditions and take a straight
route to the hospital.
MEMBERS: Kubeshavarsha Kalithasan, Anubhav Pant, Pedro Cupertino, Ami Goto, Yuto Minami
ADVISOR: Dr. Jielong Cai
ASD W45 is a short takeoff and landing (STOL) cargo drone designed in modular configuration to transport supplies to remote, urban, or disaster-stricken areas. The aircraft was developed for under $600 with model-based engineering, constraint analysis, and 3D computer-aided design to meet aggressive targets for cost, quality, and delivery. Its wood frame, 3D-printed modular payload system, and magnetic-lock cartridge allow for quick assembly and tool-free mission modification. Tested in wind tunnel and flight testing, the design attests to practical application in emergency response, urban logistics, and defense support.
MEMBERS: Sarah Varner, Nate Scarrow, Paige Nobles
ADVISOR: Dr. Jielong Cai
The team was tasked with defining a unique, valuable mission statement for the plane they designed and built. Recognizing Wichita's needs in the medical field and the various hospitals spread across the metro area and even rural Kansas, the team made a small-scale, unmanned, fixed-wing aircraft to transport and pick up organs needed for medical transplants in a secure, fast manner. The plane can take off from a short platform (a hospital helipad, for example), and fly to where the organs are located. When the plane arrives, it picks up and transports organs to another hospital via helipad or any available runway surface that is available, via cushioned, air-tight, climate-controlled, and sterile containers. This is a unique solution in the way that pilots would not be necessary for transporting the organs, and it is electric powered, saving money on fuel and labor, as well as making the aircraft lighter. By avoiding the need to drive on roads or through traffic, this plane significantly reduces the time needed to transport lifesaving organs and improves the chances of successful transplants.
MEMBERS: Julia McLaughlin, Hunter Robertson, Zachary Oakley, Jason Hildreth
ADVISOR: Dr. Jielong Cai
In the realm of Urban Air Mobility (UAM), almost every company is vying to be the best at transporting 1-4 people. While this may be an effective method to help relieve the issues with current urban transportation methods, it raises concerns about creating similar problems in the air. SpaceY presents the Robot Chicken, an electric STOL aircraft designed to take off and land in less than 15 feet, corresponding to a full scale runway of roughly 300 feet, around 6% the length of a traditional runway! Designed for efficiency, manufacturability, and repairability, this aircraft can transport 16 passengers from a rural area into a city and back as a means of daily transport reducing the number of vehicles on the road while simultaneously reducing carbon emissions. The unique lifting body fuselage maintains a lightweight and efficient profile and the modular design makes for easy disassembly for repairs and a compact form factor for ground transport. Alternate interior configurations of this aircraft also support the relocation of people, supplies and equipment during natural disasters where ground transportation is interrupted, unmanned military transport, aerial tourism, and evacuation from war zones where the established humanitarian corridors for civilians are not being properly observed.
MEMBERS: Mason Hensley, Joseph Macko, Caleb Perkins, Zephan Rodriguez, Peter Stuhlsatz
ADVISOR: Dr. Jielong Cai
In recent years, power grids in highly dense urban populations have been susceptible to long-term outages due to extreme weather. Many highly dense cities do not have the infrastructure to maintain power during these anomalies. The same can be said in war-torn regions where conflicts severely limit the ability to produce sustained power. These power disruptions not only affect households but also cripple critical infrastructure like hospitals, communication networks, and transportation systems. In times of large-scale outages, the military does not currently possess the manpower and machinery necessary to support power outages in highly dense urban populations
That is where the SS-25 Soaring Sterling fills this need in power restoration and sustainment by delivering necessary equipment and technicians to areas in need and supplying power until the region’s power grid can return online. The SS-25 is an Urban Air Mobility aircraft capable of short take-offs and landings on asphalts or on rough terrain. The SS-25 has the maneuverability and endurance necessary to fly through a highly dense urban environment to an area in need. SS-25 is meant for short notice operations with its automatic loading of a modular cargo container picking up containers such as generators underneath the belly of the aircraft. The SS-25 carrying a large payload would be a certified aircraft underneath the FAA’s Code of Federal Regulations as a Part 25 aircraft.
Stop by our booth to see the flight-tested RC aircraft prototype and try flying our aircraft in the flight simulator!
2025 (Non-Senior Design) Undergraduate Projects
MEMBERS: Caden Carlson, Gary Tran, Reese Pekny, Will Fischer
ADVISOR: Dr. Vijay Matheswaran
The Magnus effect is an aerodynamic phenomenon that describes the lift force generated by a rotating body due to asymmetric airflow and pressure distribution. This project explores the potential of integrating leading-edge rotating cylinders (LERCs), which induce the Magnus effect, into airfoil designs to enhance lift and stall characteristics, particularly at Short Take-Off and Landing (STOL) conditions. Computational analyses have shown that LERCs can significantly improve lift coefficients and stall angle of attack, particularly at low Reynolds numbers. These results have been verified through experimental low-speed wind tunnel testing. Experimental testing also showed improved boundary-layer attachment and reduced flow separation. Ground-effect in takeoff and landing performance studies emphasize the importance of lift augmentation, such as flap deployment, yet most research has not incorporated Magnus effect-based flow control mechanisms in operational flight at STOL conditions. To address these limitations, this project proposes an experimental approach incorporating a rotating cylinder airfoil model in wind tunnel testing. By measuring lift and drag coefficients, this experiment aims to provide further support for the Magnus effect’s applicability to practical aircraft designs, specifically focusing on its feasibility for air tractors and other STOL-reliant platforms.
MEMBERS: Aiden Holt, Kazune Tazawa
ADVISOR: Dr. Suresh Raju
This study investigates the torsional behavior of open-frame, skeletal structures commonly found in remote-controlled aircraft. These structural configurations are popular due to their lightweight designs; however, accurately predicting their torsional stiffness is a challenge using typical methods. Traditional torsion theories used for monocoque designs are insufficient when applied to open-frame structures due to geometric discontinuities and complicated load paths. While Finite Element Analysis can provide highly detailed solutions, it tends to be a time-consuming process, making high-speed prototyping a challenge.
To address the gap in theoretical applications, this study proposes a quick mechanics-based method to predict torsional stiffness and deformations in open-frame designs. This approach aims to bridge the gap between analytical simplicity and predictability, providing a fast and reliable estimation method. This research uses Digital Image Correlation (DIC) techniques to experimentally observe and measure the kinematics of deformation of various test samples with applied torsional loading. The evaluation of test data assists in validating the proposed model and also contributing a deeper understanding of the deformation mechanisms present in open-frame structures.
By combining experimental kinematic data with a simplified mechanical analysis, this work delivers a theoretical method for understanding and predicting torsional performance in remote-controlled aircraft utilizing open-frame, skeletal designs with efficiency and accuracy.
MEMBERS: Alyssa Rutherford, Ella Kreger, Kellsie Juhl
ADVISOR: Dr. Vijay Matheswaran
This work analyzes a model of the Common Loon in a 3 x 4 wind tunnel. Loons are exceptional swimmers with unique adaptations that enhance their diving ability. Part of this adaptation is the Loon’s power stroke sequence, which is how they move so well through the water. They have a symmetrical stroke, meaning both feet move in sync. This stroke begins in the forwardmost position with the webbing of their feet slightly extended. Then, as they push their feet back, they fully extend this webbing to produce the most thrust. Finally, they tuck their feet back behind them after completing the stroke to minimize drag as they cruise through the water using the produced thrust. For this experiment, we tested 4 foot positions at different stations of the power stroke to determine its impact on drag. Throughout the project, we collaborated with Dr. James Paruk, a Professor at St. Joseph’s College and a Common Loon expert with 23+ years of research experience.
MEMBERS: Catalina Blair, Kenil Patel, Riley Strandberg, Lane Sherbert
ADVISOR: Dr. Vijay Matheswaran
The Schottky-Klein prime function is a special function in complex analysis. One application of the function is fluid dynamics, specifically the fluid flow around multi-element airfoils. This is highlighted in a 2023 paper by Thomas DeLillo and Christopher Green. Utilizing a NACA4415 airfoil with three elements, the method in the paper is compared to experimental coefficients of pressure at a variety of flap deflection angles and angles of attack. This is done to see when the method is most accurate, and when it is no longer applicable.
MEMBERS: Parker Struve, Seth Newton, James Wright, Joshua Amiegbebhor-Onikolase
ADVISOR: Dr. Vijay Matheswaran
The team conducted a study of the Supersonic Bi-Directional (SBiDir) Flying Wing design created by the University of Miami. The University of Miami primarily carried out Computational Fluid Dynamics (CFD) analyses of the design in supersonic flight. This led the team to ask if the SBiDir design would be feasible in the subsonic flight regime. Since this craft is primarily designed as a supersonic transport, the only occurrences of subsonic flight the team could reasonably test are in takeoff and landing, leading to the study of ground effect becoming the primary consideration of the project. The team 3D printed the design out of PETG and carried out post-processing to remove the roughness from the skin caused by the printing. The team then used the WSU 3x4 wind tunnel to test the baseline cruise performance by obtaining the Lift, Drag, and Pitching Moment Coefficients as functions of angle of attack. An artificial ground plane was then introduced to the tunnel to simulate the aircraft coming close to the ground. The team tested several different distances between the ground plane and the model at various angles of attack to again obtain the Lift, Drag, and Pitching moment coefficients. The data obtained was then plotted and compared to determine what effect the ground has on the aircraft. Specifically, the team was most concerned with how the Lift to Drag ratios would compare to determine the effect of the ground on the lift and drag forces generated in the tunnel.
MEMBERS: Austin Sanderson, Clayton Crockett, Cole Matthews, Kylen Divelbiss
ADVISOR: Dr. Vijay Matheswaran
Aircraft in supersonic flight experience shock wave formation, which adversely affects aerodynamic performance. Wave drag is a consequence of shock wave formation and is inherently linked to the increase in entropy, resulting from the loss of total pressure across the oblique shock waves generated by the airfoil. Shock control bumps have been very successful in promising performance potential and practicality, by reducing wave drag, when used correctly. These benefits are apparent in mostly transonic conditions, with a knowledge gap in effectivity for supersonic applications. This study aims to combine previous efforts in manipulating flow for aerodynamic performance, with a focus on shock control bumps to reduce wave drag.
MEMBERS: Isaac Thompson, Silja Fahnestock, Jordan Lower, Kelsey Thurman
ADVISOR: Dr. Vijay Matheswaran
This project is testing the effectiveness of several inlet bump designs based on pressure coefficient profiles and shock wave patterns. Mock up 2D profiles will be tested in a water table. During testing water heights will be collected at various points and pictures will be taken to determine pressure and shock wave angles throughout the test section. Using this data, pressure coefficients, Mach numbers, and shock wave patterns can be found and analyzed.
MEMBERS: Luke Cotter, Treyton Blecke
ADVISOR: Dr. Jielong Cai
SPONSOR: NASA in Kansas
Traditional quadcopter drones use pitch control to achieve forward flight. However, pitching the drone body causes inefficiencies in the form of downforce and drag. This study looks to compare the efficiency of traditional and alternative drone designs. To achieve this end, A numerical model was built from wind tunnel data of rotor characteristics at varying angles of attack. The model measures the thrust and pitching moments of individual rotors to determine the combination of rotor speeds to keep the drone pitch and altitude stable. This model uses the determined rotor RPM to estimate the power consumption of the drone. To view the efficiency of each drone design, the power consumption for each drone design is plotted on the same axes. The study focuses on comparing the traditional free-to-pitch design to a 5-rotor, fixed-pitch drone and a tiltrotor fixed-pitch drone. Power consumption is measured for drones of varying weight, cruise velocity, and center of gravity location.
MEMBERS: Jed Cole, John Cummings, Rylan Fay, Jacob Walden
ADVISOR: Dr. Vijay Matheswaran
Our study aimed to optimize the rear wing layout of an FSAE car by maximizing lift-to-drag (L/D) ratio. The team investigated how changing the position and angle of attack of the small elements influence the aerodynamic efficiency. All wing elements used an S1123 airfoil. Looking at position, we adjusted the Gap-to-Chord (G/C) ratio, testing at values ranging from 0.05 to 0.20, as anything higher than 0.20 causes flow separation. The team also chose to adjust the angle of attack of the two rear elements, these are tested at values ranging from -10 degrees to 42 degrees, relative to the previous element. These values were chosen based on previous FSAE experience and some basic CFD calculations. Our data was collected mainly through wind tunnel testing, with some CFD simulations to confirm testing values. Our results will directly influence the rear wing design improvements for the WSU FSAE team.
MEMBERS: Surajkumar Vaddy, Colton Hill, Cole Cumberland, Richard Kaiser
ADVISOR: Dr. Vijay Matheswaran
Our testing aims to determine the maximum lift-to-drag ratio (L/D) of the front wing-wheel assembly of the WSU Formula SAE 2025 vehicle after modifying it. To achieve this, the secondary wing elements will be rotated along the longitudinal axis, and data will be collected to analyze the impact of this change on L/D. The specific testing objectives of this experiment are as follows:
1) The wheel will be mounted separately from the front wing as the focus of the experiment is to reduce the drag of tire.
2) To find the drag acting on the wheel (isolated rotating wheel, with un-modified front wing, and with modified front wing)
3) To determine the lift acting on the wheel for different modifications.
4) To determine the downforce acting on the front wing for each modification
5) To determine the drag acting on the front wing for each modification.
MEMBERS: Holden Goertzen, Sarah Varner, Erik Andersen, Brylea Schmidt
ADVISOR: Dr. Vijay Matheswaran
SPONSOR: International Inc., Illinois
Our team has been fortunate enough to conduct a specific experiment with International Motors Inc. This testing occured in the National Institute for Aviation Research sub-sonic 7’x10’x12’ Beech Wind Tunnel. The team designed, prototyped, and tested an active flow control (AFC) drag reduction system (DRS) by modification of semi-truck side extender flaps. Said flaps were required to move and hold at set angles for wind tunnel testing via an internal motorized system. An electronic prototyping platform (Arduino Uno) micro-controller was used to send and receive set commands. A pressure scanner collected pressure information from two pressure ports located on the front of the model for side slip calculation. This hardware was mounted directly to the customer wind tunnel model, primarily between the tractor and trailer components. Testing was integrated seamlessly with the customer test matrix as this system can be installed/uninstalled in a short amount of time. A test matrix consisting of four primary blocks was run for testing. Beta sweeps ~(-15˚< β < 15˚) with the AFC system fixed at 0˚ deflection for baseline characterization. Flap sweeps at constant Beta (vehicle side slip angles) for flap effect characterization. Data reduction and analysis to derive a drag optimization algorithm relating flap deflection to drag reduction. Lastly, randomized Beta sweeps with activated DRS running optimization algorithm. The team analyzed the wind tunnel data, primarily drag/axial force, to determine the effectiveness of the DRS.
MEMBERS: Morgan Scott, Jude Swilley, Connor O'Dwyer, Cole Jackson
ADVISOR: Dr. Vijay Matheswaran
The aerodynamic performance of delta wings in supersonic flight is primarily influenced
by sweep angles and wing configuration. Each of these parameters has an impact on
the formation of shockwave structures, as well as the strength of each shock. Shockwaves
generate pressure spikes, directly affecting how wave drag forces act upon a wing.
This results in shockwave structure formation becoming a critical component when attempting
to minimize drag. The objective of this study is to examine if a 50 degree swept delta
wing configuration offers any advantages over a more conventional and proven 60 degree
sweep. These advantages include weaker shocks or smaller shock angles, which correspond
to reduced drag. In addition, a lower sweep angle is known to increase the lift-to-drag
ratio, which could be very beneficial at lower speeds, where delta wings struggle
to generate lift. Utilizing water table flow visualization techniques, three different
variations of delta wing will be tested: cropped, ogival, and tailed. Each configuration
will be evaluated at both 50 and 60 degree sweep angles, with the latter functioning
as a control element. The water table experimentation will analyze the behavior of
shockwaves at specific supersonic Mach numbers, including the shockwave structure,
intensity, and angle. Preliminary theoretical calculations will be performed, and
then compared to the resultant experimental data to ensure validity as well as examine
any possible deviations. Through the investigation of lower sweep angles, this study
aims to challenge the notion that 60-degree swept
wings are the optimal design for supersonic flight.
MEMBERS: Tyler Roush, Zach Saffell, Jonathan Wessel, Maggie Karashani
ADVISOR: Dr. Vijay Matheswaran
Wing tips have long been an area of interest in the pursuit of aircraft efficiency. Namely, wing tips have been used to control the size and shape of wing tip vortices. Wing tip vortices play a key role in induced drag. At non-zero lift angles of attack, a finite wing will generate wing tip vortices as a result of the pressure differential between the upper and lower surfaces of the wing. The vortices produce a downwash which results in an additional drag component. This study aims at reducing this induced drag by means of a span wise pitching symmetric reverse half delta wing tip. The Reverse Half-Delta Wingtip (RHDWT) will remain at zero Angle of Attack (AOA), while the rectangular cambered half span wing will vary from –5° to 15° AOA. This configuration will be tested at a Re of 2.5x105 and a q of 4.8 psf. This study aims to increase the (CL/CD)max value. On-surface flow visualization will also be used to observe the crossflow pattern on the wing surface near the wing tip.
MEMBERS: Nathaniel Boyer, Caden Dresher, Patrick Mack, Xavier Villagrasa
ADVISOR: Dr. Vijay Matheswaran
This design project investigates the impact of incorporating multiple porosities on a NACA0012 airfoil, focusing on the performance implications of applying a fully porous upper surface. The study is inspired by a NASA research project that explored the effects of a porous upper surface on an airfoil, specifically within a Mach number range of 0.50 to 0.82 and chord Reynolds numbers of 2 x 10^6, 4 x 10^6, and 6 x 10^6. The NASA study revealed that the porous NACA0012 exhibited self-adaptive characteristics, enhancing its performance to resemble that of a high-speed airfoil. In contrast, this project examines the behavior of a similar airfoil under incompressible flow conditions, aiming to evaluate its aerodynamic performance at lower speeds where the self-adaptive features identified in the NASA study may not be present. The goal is to better understand the advantages and limitations of using a porous upper surface on the NACA0012 airfoil in incompressible flow.
MEMBERS: Kaden Scheuler, Don Boyd, Marcos Gomez-Hernendez
ADVISOR: Dr. Vijay Matheswaran
The comparison between pressure distributions around two elevated water towers. Spherical and cylindrical tank pressure data will be taken, plotted and compared between the two will be made.
MEMBERS: Manuel Salamanca, Isai Waboshi, Benny Godwin, Dhruv Roy
ADVISOR: Dr. Vijay Matheswaran
The objective of this study is to analyze the aerodynamic performance of wing fences as lateral control surfaces, which could enhance the stability and control authority of flying wings. By varying both the deflection angle of the wing fences and the angle of attack for a finite wing, this experiment aims to improve control by redirecting airflow over the upper surface of the wing. The parameters intended to remain constant are the wing and wing fence airfoil, Reynolds number, free stream velocity, and number of wing fences. Using the six-axis setup in the 3’x4’ wind tunnel, forces experienced by the wing will be measured and characterized. The six-axis system will collect data on the forces and moments experienced by the body-fixed axis which will be converted into aerodynamic forces and moments. The primary goal of this investigation is to explore the feasibility of deflecting wing fences to generate an additional degree of motion in the lateral direction and to analyze how the spanwise flow changes with different deflection angles.
MEMBERS: Lucas Baker, Kubeshavarsha Kalithasan, Mason Hensley, Caleb Perkins, Hunter Robertson, Jonathan Spachek, Peter Stuhlsatz
ADVISOR: Dr. Atri Dutta
The International Rocketry Engineering Competition (IREC) is the largest collegiate rocketry competition in the world. The Wichita State Rocket Club entered the 2025 IREC with the rocket project titled Ad Astra. The category the team will be competing in is 10,000 ft. Commercial Off The Shelf (COTS). Therefore, the mission of Project Ad Astra is to reach precisely 10,000 ft. on a COTS motor. The Wichita State Rocket Club competed in the IREC competition 10,000 ft. COTS category for the first time in 2024 achieving an altitude of 10,019 ft. on all COTS components with a boilerplate payload. The engineering design objective for project Ad Astra is to create more Student Researched and Developed (SRAD) components through rigorous testing and detailed documentation. This includes designing and manufacturing an SRAD flight computer, airbrakes, and livestreaming electronics. Project Ad Astra will also house a boilerplate 1U CubeSat. The Wichita State Rocket Club's goal for Project Ad Astra is to extend the members’ classroom knowledge of engineering to a hands-on project working as a team to successfully complete the mission objective and achieve a higher score in competition than the previous year.
2025 (Non-Senior Design) Graduate Projects
MEMBER: Adam Bodenham
ADVISOR: Dr. Charles Yang
This applied learning activity seeks to draw conclusions about two methods of calculating the failure of a cracked specimen: fracture toughness and strain energy release rate. Strain energy release rate methods are common in very brittle materials, like those used in the analysis of ice, rock, and concrete. Alloyed aluminums used in aerospace, like 7050-T651 plate, do exhibit brittle failure surfaces. Applying strain energy release rate criteria, a standard corner edge through thickness crack in an aluminum sample can therefore be compared with the industry standard fracture toughness criteria. The comparison of these two valid methods is explored in this project. An energy formulation can be developed for the sample based on the internal strain energy. The results of which are compared with those from a model using fracture toughness and stress intensity calculations. The initial flaw size will be varied and the corresponding applied stress at failure will be compared.
MEMBER: Azizbek Uktamjonov
ADVISOR: Dr. Chihdar C. Yang
This study investigates the effects test set up deviations from standard procedure (ASTM D6641), such as bolt torque mismatch, coupon preload, tabbed and unstabbed coupon types on stress-strain curves in combined load compression (CLC) tests. Finite Element analysis has been used to obtain stress-strain curves for said variations based on FE material parameters developed based on physical tests.
MEMBER: Shasthick Mohanraj
ADVISOR: Dr. Chihdar C. Yang
Mesh sensitivity plays a critical role in determining result accuracy, convergence behavior, and computational efficiency. This study focuses on the numerical simulation of QSI using LS-DYNA, to investigate how mesh density influences the accuracy and reliability of the outputs. For this simulation material model MAT-58 was used to represent a laminated composite, with mesh sizes varying from 0.2 mm to 18 mm. The test setup consisted of a fixture modeled with Aluminum and Steel solid elements and the composite laminate is modeled using shell elements. Peak load, displacement, and energy absorption were observed across different mesh sizes. The results from the test commensurate with the simulation results of mesh size 5. Mesh sizes below 3 mm cause element erosion and fluctuations in load response due to shear locking effects. The internal energy of the laminate and fixture is notably higher for Mesh Sizes 2 and 3 compared to other mesh sizes. This increase in the laminate’s internal energy is attributed to the inclusion of interface energy for finer mesh. As mesh size increased beyond 5 mm, peak load and displacement values also increased indicating reduced accuracy. The findings highlight that while finer meshes might appear to offer greater detail, they can introduce artifacts that reduces the reliability of the results. Also, Finer mesh sizes resulted in higher computational costs and longer simulation times, making them less suitable for iterative analyses or large-scale simulations. A 5 mm mesh was identified as optimal, providing a balance between computational efficiency and reliable simulation results. This study helps choose the right mesh size for accurate and stable composite impact simulations.