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Articles 1 - 30 of 317
Full-Text Articles in Aerospace Engineering
Comparisons Of Cooling Performance And Flow Characteristics Of A Combustor Liner Plate With Compound Angle And Simple Angle Effusion Holes, Hwabhin Kwon, Phillip M. Ligrani, Sneha R. Vanga, Heesung Park
Comparisons Of Cooling Performance And Flow Characteristics Of A Combustor Liner Plate With Compound Angle And Simple Angle Effusion Holes, Hwabhin Kwon, Phillip M. Ligrani, Sneha R. Vanga, Heesung Park
PRC-Affiliated Research
The present investigation considers a unique compound angle arrangement, never previously considered, with α = 30°, β = ±30°, such that the compound angle of the effusion holes changes from β = +30° to β = −30°, as adjacent rows of effusion holes are encountered. Also provided are data for comparison from a simple angle configuration with α = 30°, β = 0°. Coolant is supplied to both effusion hole arrays using arrays of impingement cooling jets. The results of the numerical simulations are obtained using the ANSYS FLUENT V 21.1 numerical code, with a shear stress transport (SST) k–ω …
Effects Of Pressure Side Film Cooling Hole Placement And Condition On Surface Heat Transfer Characteristics Of A Transonic Turbine Blade Tip, Hallie Collopy, Phillip M. Ligrani, Hongzhou Xu, Michael Fox
Effects Of Pressure Side Film Cooling Hole Placement And Condition On Surface Heat Transfer Characteristics Of A Transonic Turbine Blade Tip, Hallie Collopy, Phillip M. Ligrani, Hongzhou Xu, Michael Fox
PRC-Affiliated Research
The effects of film cooling hole placement location along the upper pressure side of a transonic squealer are considered. The thermal performance of four different film cooling configurations; B1, B2, B3 and B4, are considered using the University of Alabama in Huntsville's SS/TS/WT (supersonic/transonic/wind tunnel) experimental facility and a simulated turbine blade row using a linear cascade. Surface-varying results are provided for both the squealer blade tip surface, and for the upper pressure side of the squealer blade. These results are given for blowing ratios ranging from 0.42 to 3.20 in the form of spatially-resolved and spatially-averaged adiabatic film cooling …
Feasibility Of Low-Enriched Uranium Fueled Nuclear Thermal Propulsion In The Low-Thrust Region Below 16klbf, Samantha B. Rawlins, Dale L. Thomas
Feasibility Of Low-Enriched Uranium Fueled Nuclear Thermal Propulsion In The Low-Thrust Region Below 16klbf, Samantha B. Rawlins, Dale L. Thomas
PRC-Affiliated Research
No abstract provided.
Development Of A Trailing Edge Flap Using A Compliant Mechanism, Matthew Maybee
Development Of A Trailing Edge Flap Using A Compliant Mechanism, Matthew Maybee
Summer Community of Scholars Posters (RCEU and HCR Combined Programs)
No abstract provided.
Creation And Development Of An Obstacle Database For Uas Pathfinding, Cameron Clarke
Creation And Development Of An Obstacle Database For Uas Pathfinding, Cameron Clarke
Summer Community of Scholars Posters (RCEU and HCR Combined Programs)
No abstract provided.
Mitigation Of The Laminar Separation Bubble Using Active Vortex Generators, Hayden Hitt
Mitigation Of The Laminar Separation Bubble Using Active Vortex Generators, Hayden Hitt
Summer Community of Scholars Posters (RCEU and HCR Combined Programs)
No abstract provided.
Flow And Heat Transfer In Swirl Tubes — A Review, Florian Seibold, Phillip M. Ligrani, Bernhard Weigand
Flow And Heat Transfer In Swirl Tubes — A Review, Florian Seibold, Phillip M. Ligrani, Bernhard Weigand
PRC-Affiliated Research
The development of modern gas turbines for aircraft propulsion and power generation demands ever-increasing efficiency, which can be achieved by rising the turbine inlet temperature. Therefore, turbine components and especially the leading edge of turbine blades are exposed to particular high thermal loads with temperatures that are well above the melting point of the material. As a result, efficient cooling techniques are essential. Swirling flows in cyclone cooling systems are a promising technique for internal turbine blade leading edge cooling since they promise high heat transfer rates in combination with relatively uniform heat transfer distributions. The current paper presents a …
Using An Ultrasonic Technique To Determine Burning Rate Law, Brennan Hatton Haralson
Using An Ultrasonic Technique To Determine Burning Rate Law, Brennan Hatton Haralson
Honors Capstone Projects and Theses
No abstract provided.
Performance Variability In Solid Rocket Motors, Manvith Amara
Performance Variability In Solid Rocket Motors, Manvith Amara
Honors Capstone Projects and Theses
No abstract provided.
Rotating Detonation Rocket Engine Fluidic Diode Injector Studies, Allison Brooke Lentz
Rotating Detonation Rocket Engine Fluidic Diode Injector Studies, Allison Brooke Lentz
Honors Capstone Projects and Theses
No abstract provided.
Computational Plasma Modeling For Characterization Of An Atmospheric Pressure Plasma Jet, Declan George Brick
Computational Plasma Modeling For Characterization Of An Atmospheric Pressure Plasma Jet, Declan George Brick
Honors Capstone Projects and Theses
No abstract provided.
Honor Capstone Lunar Logistics Study, Owen Bradley Cox
Honor Capstone Lunar Logistics Study, Owen Bradley Cox
Honors Capstone Projects and Theses
No abstract provided.
Design And Analysis Of A Pitch Controller For An Unstable Aircraft Using A Linear Quadratic Regulator, Marco Antonio Garcia
Design And Analysis Of A Pitch Controller For An Unstable Aircraft Using A Linear Quadratic Regulator, Marco Antonio Garcia
Honors Capstone Projects and Theses
No abstract provided.
Development Of A Bio-Inspired Artificial Butterfly Vehicle, Thomas Payne Clark
Development Of A Bio-Inspired Artificial Butterfly Vehicle, Thomas Payne Clark
Honors Capstone Projects and Theses
No abstract provided.
Wildfire Updrafts And Downdrafts Effects Of Aerial Vehicles Flight Mechanics, Connor Flynn
Wildfire Updrafts And Downdrafts Effects Of Aerial Vehicles Flight Mechanics, Connor Flynn
Honors Capstone Projects and Theses
No abstract provided.
Experimental Study Of Turbulent Flow Heat Transfer And Pressure Loss Over Surfaces With Dense Micro-Depth Dimples Under Viscous Sublayer, Peng Zhang, Yu Rao, Phillip M. Ligrani
Experimental Study Of Turbulent Flow Heat Transfer And Pressure Loss Over Surfaces With Dense Micro-Depth Dimples Under Viscous Sublayer, Peng Zhang, Yu Rao, Phillip M. Ligrani
PRC-Affiliated Research
Presented are experimentally-measured heat transfer and pressure loss characteristics for dimpled surfaces, placed along one surface of a channel, with different ratios of dimple depth to channel height δ/H, and for Reynolds numbers ranging from 10,000 to 70,000. With the same relative dimple spacing to dimple print diameter, and the same ratio of dimple depth to dimple print diameter of δ/d = 0.20, experimental results for arrays of spherical indentation dimples with micro depths of δ = 0.6 and 1.0 mm (δ/H = 0.03 and 0.05) are compared with thermal characteristics for arrays of larger dimples with δ = 4.0 …
Flow Structure And Surface Heat Transfer From Numerical Predictions For A Double Wall Effusion Plate With Impingement Jet Array Cooling, Hwabhin Kwon, Phillip M. Ligrani, Sneha Reddy Vanga, Heesung Park
Flow Structure And Surface Heat Transfer From Numerical Predictions For A Double Wall Effusion Plate With Impingement Jet Array Cooling, Hwabhin Kwon, Phillip M. Ligrani, Sneha Reddy Vanga, Heesung Park
PRC-Affiliated Research
To provide additional understanding of double wall cooling arrangements, especially local distributions of flow properties which are responsible for hot-side surface and cold-side surface heat transfer variations, investigated are numerically-simulated distributions of turbulent flow structural characteristics. Also considered are numerically-simulated surface heat transfer characteristics, including comparisons with experimentally-measured distributions. The numerical results are obtained using the ANSYS FLUENT Version 19.1 numerical code, with a k-ω SST turbulence model. The present arrangement includes a full-coverage effusion cooling plate, with coolant initially supplied by an impingement jet array. Considered are the effects of effusion blowing ratio, impingement jet Reynolds number, and streamwise …
Flow And Heat Transfer Characteristics In A Pre-Swirl Rotor-Stator Cavity, Xiaoyu Yang, Zhong Ren, Jing Ren, Philip M. Ligrani
Flow And Heat Transfer Characteristics In A Pre-Swirl Rotor-Stator Cavity, Xiaoyu Yang, Zhong Ren, Jing Ren, Philip M. Ligrani
PRC-Affiliated Research
The present study investigates flow and heat transfer characteristics in a rotor-stator pre-swirl system. Considered are rotational Reynolds numbers ReФ ranging from 3.4 × 105 to 6.8 × 105, with jet Reynolds numbers Rew of approximately 8.8 × 104 to 3.81 × 105, and associated turbulent flow parameter λT = Cw/ReФ0.8 varying from 0 to 0.4. Experimentally-measured and numerically-predicted results illustrate the combined and separate influences of jet impingement and rotor entrainment, as they affect and govern flow and heat transfer characteristics within the cavity. These results show that the relative strength of the two effects varies with ReФ and …
Characterization Of Effective Diffusion Within Viscoelastic Fluids With Elastic Instabilities, Valerie Hietsch, Phillip Ligrani, Mengying Su
Characterization Of Effective Diffusion Within Viscoelastic Fluids With Elastic Instabilities, Valerie Hietsch, Phillip Ligrani, Mengying Su
PRC-Affiliated Research
We considered effective diffusion, characterized by magnitudes of effective diffusion coefficients, in order to quantify mass transport due to the onset and development of elastic instabilities. Effective diffusion coefficient magnitudes were determined using different analytic approaches, as they were applied to tracked visualizations of fluorescein dye front variations, as circumferential advection was imposed upon a flow environment produced using a rotating Couette flow arrangement. Effective diffusion coefficient results were provided for a range of flow shear rates, which were produced using different Couette flow rotation speeds and two different flow environment fluid depths. To visualize the flow behavior within the …
Uas Obstacle Database For University Traffic Management System, Casey Calamaio
Uas Obstacle Database For University Traffic Management System, Casey Calamaio
Summer Community of Scholars (RCEU and HCR) Project Proposals
No abstract provided.
Design And Development Of Active Flow Effectors, Konstantinos Kanistras
Design And Development Of Active Flow Effectors, Konstantinos Kanistras
Summer Community of Scholars (RCEU and HCR) Project Proposals
No abstract provided.
Design And Development Of An Online Wind Tunnel, Konstantinos Kanistras
Design And Development Of An Online Wind Tunnel, Konstantinos Kanistras
Summer Community of Scholars (RCEU and HCR) Project Proposals
No abstract provided.
Small Hall Effect Thruster With 3d Printed Discharge Channel: Design And Thrust Measurements, Ethan P. Hopping, Wensheng Huang, Kunning G. Xu
Small Hall Effect Thruster With 3d Printed Discharge Channel: Design And Thrust Measurements, Ethan P. Hopping, Wensheng Huang, Kunning G. Xu
PRC-Affiliated Research
Citation: Hopping, E.P.; Huang, W.; Xu, K.G. Small Hall Effect Thruster with 3D Printed Discharge Channel: Design and Thrust Measurements. Aerospace 2021, 8, 227. https:// Abstract: This paper presents the design and performance of the UAH-78AM, a low-power small Hall effect thruster. The goal of this work is to assess the feasibility of using low-cost 3D printing to create functioning Hall thrusters, and study how 3D printing can expand the design space. The thruster features a 3D printed discharge channel with embedded propellant distributor. Multiple materials were tested including ABS, ULTEM, and glazed ceramic. Thrust measurements were obtained at the …
Small Hall Effect Thruster With 3d Printed Discharge Channel: Design And Thrust Measurements, Ethan P. Hopping, Wensheng Huang, Kunning G. Xu
Small Hall Effect Thruster With 3d Printed Discharge Channel: Design And Thrust Measurements, Ethan P. Hopping, Wensheng Huang, Kunning G. Xu
PRC-Affiliated Research
Citation: Hopping, E.P.; Huang, W.; Xu, K.G. Small Hall Effect Thruster with 3D Printed Discharge Channel: Design and Thrust Measurements. Aerospace 2021, 8, 227. https:// Abstract: This paper presents the design and performance of the UAH-78AM, a low-power small Hall effect thruster. The goal of this work is to assess the feasibility of using low-cost 3D printing to create functioning Hall thrusters, and study how 3D printing can expand the design space. The thruster features a 3D printed discharge channel with embedded propellant distributor. Multiple materials were tested including ABS, ULTEM, and glazed ceramic. Thrust measurements were obtained at the …
Plasma-Based Water Purification For Crewed Space Missions: Laboratory Experimental Comparisons For On-Board Applicability, Ryan P. Gott, Sydney D. Miller, Josie C. Hodges, Kunning G. Xu
Plasma-Based Water Purification For Crewed Space Missions: Laboratory Experimental Comparisons For On-Board Applicability, Ryan P. Gott, Sydney D. Miller, Josie C. Hodges, Kunning G. Xu
PRC-Affiliated Research
Low-temperature, atmospheric pressure plasma presents a new, inexpensive, and environmentally friendly method of water purification. For long duration crewed space missions, a novel water purification system that does not rely on consumable filters and chemicals would be desirable. Plasma systems provide a viable option for these missions, but their operation and designs need to be optimized and compared to existing technology. For this application, gas and power usage are key limiting factors. In this work, water contaminated with methylene blue is purified with plasma. The rate of purification, gas flow usage, and power consumption are compared for multiple devices. A …
Plasma-Based Water Purification For Crewed Space Missions: Laboratory Experimental Comparisons For On-Board Applicability, Ryan P. Gott, Sydney D. Miller, Josie C. Hodges, Kunning G. Xu
Plasma-Based Water Purification For Crewed Space Missions: Laboratory Experimental Comparisons For On-Board Applicability, Ryan P. Gott, Sydney D. Miller, Josie C. Hodges, Kunning G. Xu
PRC-Affiliated Research
Low-temperature, atmospheric pressure plasma presents a new, inexpensive, and environmentally friendly method of water purification. For long duration crewed space missions, a novel water purification system that does not rely on consumable filters and chemicals would be desirable. Plasma systems provide a viable option for these missions, but their operation and designs need to be optimized and compared to existing technology. For this application, gas and power usage are key limiting factors. In this work, water contaminated with methylene blue is purified with plasma. The rate of purification, gas flow usage, and power consumption are compared for multiple devices. A …
Thermochemistry Of Combustion In Polyvinyl Alcohol + Hydroxylammonium Nitrate, James K. Baird, Robert A. Frederick Jr.
Thermochemistry Of Combustion In Polyvinyl Alcohol + Hydroxylammonium Nitrate, James K. Baird, Robert A. Frederick Jr.
PRC-Affiliated Research
A mixture of polyvinyl alcohol (PVA) and hydroxylammoniun nitrate (HAN) forms a gummy solid known as a plastisol, which is ionically conducting. When an electrostatic potential of 200 V DC is applied across the plastisol, it ignites. Combustion ceases upon removal of the applied voltage. The products of PVA + HAN combustion are known to include the molecular gases carbon monoxide, carbon dioxide, water, nitrogen, and hydrogen. When the electric field within the plastisol is spatially uniform, combustion occurs preferentially at the anode. The fact that HAN is an ionic conductor suggests that the mechanism of combustion is electrolytic in …
Thermochemistry Of Combustion In Polyvinyl Alcohol + Hydroxylammonium Nitrate, James K. Baird, Robert A. Frederick Jr.
Thermochemistry Of Combustion In Polyvinyl Alcohol + Hydroxylammonium Nitrate, James K. Baird, Robert A. Frederick Jr.
PRC-Affiliated Research
A mixture of polyvinyl alcohol (PVA) and hydroxylammoniun nitrate (HAN) forms a gummy solid known as a plastisol, which is ionically conducting. When an electrostatic potential of 200 V DC is applied across the plastisol, it ignites. Combustion ceases upon removal of the applied voltage. The products of PVA + HAN combustion are known to include the molecular gases carbon monoxide, carbon dioxide, water, nitrogen, and hydrogen. When the electric field within the plastisol is spatially uniform, combustion occurs preferentially at the anode. The fact that HAN is an ionic conductor suggests that the mechanism of combustion is electrolytic in …
Rocket Flight Simulation With Monte Carlo Uncertainty Analysis, Jonathan Wallace Drake
Rocket Flight Simulation With Monte Carlo Uncertainty Analysis, Jonathan Wallace Drake
Honors Capstone Projects and Theses
No abstract provided.
Spatial Coherence Of Low-Frequency Unsteadiness Associated With A Normal Shock Wave, Matthew Cox, Phillip M. Ligrani, Kyle Goethals
Spatial Coherence Of Low-Frequency Unsteadiness Associated With A Normal Shock Wave, Matthew Cox, Phillip M. Ligrani, Kyle Goethals
PRC-Affiliated Research
The present data illustrate a unique analysis approach to explore the physics of shock-wave-flow interactions, based upon correlation and spectral analysis of digitized shadowgraph visualization time-sequence data. As such, demonstration is provided of the use of high resolution, flow visualization data for quantitative correlation and spectral analysis. A shadowgraph system is employed to visualize time-varying, shock wave flow features within the test section of one leg of the transonic/supersonic wind tunnel (which is also referred to as the SS/TS/WT or SuperSonic/TranSonic/WindTunnel), located within the Propulsion Research Center of the University of Alabama in Huntsville. Of interest is a flow field …