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Dissertations / Theses on the topic 'Aerospace engineering. Fluid mechanics. Fluid dynamics'

Author: Grafiati

Published: 4 June 2021

Last updated: 5 February 2022

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1

Chhunchha, Aakash C. "Aerodynamic Heating Analysis of Re-entry Space Capsule Using Computational Fluid Dynamics." Thesis, California State University, Long Beach, 2018. http://pqdtopen.proquest.com/#viewpdf?dispub=10752510.

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The present study deals with solving two-dimensional Reynolds Averaged Navier-Stokes equations for the Fire II re-entry capsule using Computational Fluid Dynamics (CFD). The primary goal is to model the aero thermodynamic flow characteristics around the capsule and estimate the surface heat flux distribution. Mach number value of 15.16 is chosen as a free stream condition corresponding to an altitude of 50 km. Taking advantage of the symmetry, only a quarter portion of the geometry is considered to generate the volume mesh for the simulation. The numerical models and convergence techniques that are implemented by the CFD solver are thoroughly described.

Special attention has been paid to validate the code. The value of shock stand-off distance obtained by means of benchmark empirical formulation is compared to the CFD analysis. An additional comparison between the simulated results and the approximated engineering correlations of convective stagnation point heat fluxes is made to ensure the validity of the obtained results. Overall, a satisfactory agreement is observed between the estimated values by engineering correlations and those predicted by the numerical solver.

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2

Doucet, Daniel Joseph. "Measurements of Air Flow Velocities in Microchannels Using Particle Image Velocimetry." Case Western Reserve University School of Graduate Studies / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=case1333675768.

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3

Hammargren, Kristoffer. "Aerodynamics Modeling of Sounding Rockets : A Computational Fluid Dynamics Study." Thesis, Luleå tekniska universitet, Strömningslära och experimentell mekanik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-70551.

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4

Bennett, William Thomas. "Computational and Experimental Investigations into Aerospace Plasmas." Wright State University / OhioLINK, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=wright1212780703.

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5

McGillivray, Nathan T. "Coupling Computational Fluid Dynamics Analysis and Optimization Techniques for Scramjet Engine Design." Wright State University / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=wright1536311445147862.

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6

Henricks, Quinten Michael. "Computational Aerodynamic and Aeroacoustic Study of Small-Scale Rotor Geometries." The Ohio State University, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=osu1546618814905583.

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7

Lane, Kevin A. "Novel Inverse Airfoil Design Utilizing Parametric Equations." DigitalCommons@CalPoly, 2010. https://digitalcommons.calpoly.edu/theses/346.

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The engineering problem of airfoil design has been of great theoretical interest for almost a century and has led to hundreds of papers written and dozens of methods developed over the years. This interest stems from the practical implications of airfoil design. Airfoil selection significantly influences the application's aerodynamic performance. Tailoring an airfoil profile to its specific application can have great performance advantages. This includes considerations of the lift and drag characteristics, pitching moment, volume for fuel and structure, maximum lift coefficient, stall characteristics, as well as off-design performance. A common way to think about airfoil design is optimization, the process of taking an airfoil and modifying it to improve its performance. The classic design goal is to minimize drag subject to required lift and thickness values to meet aerodynamic and structural constraints. This is typically an expensive operation depending on the selected optimization technique because several flow solutions are often required in order to obtain an updated airfoil profile. The optimizer requires gradients of the design space for a gradient-based optimizer, fitness values of the members of the population for a genetic algorithm, etc. An alternative approach is to specify some desired performance and find the airfoil profile that achieves this performance. This is known as inverse airfoil design. Inverse design is more computationally efficient than direct optimization because changes in the geometry can be related to the required change in performance, thus requiring fewer flow solutions to obtain an updated profile. The desired performance for an inverse design method is specified as a pressure or velocity distribution over the airfoil at given flight conditions. The improved efficiency of inverse design comes at a cost. Designing a target pressure distribution is no trivial matter and has severe implications on the end performance. There is also no guarantee a specified pressure or velocity distribution can be achieved. However, if an obtainable pressure or velocity distribution can be created that reflects design goals and meets design constraints, inverse design becomes an attractive option over direct optimization. Many of the available inverse design methods are only valid for incompressible flow. Of those that are valid for compressible flow, many require modifications to the method if shocks are present in the flow. The convergence of the methods are also greatly slowed by the presence of shocks. This paper discusses a series of novel inverse design methods that do not depend on the freestream Mach number. They can be applied to design cases with and without shocks while not requiring modifications to the methods. Shocks also do not have a significant impact on the convergence of the methods. Airfoils are represented with parametric equations from the CST method to control shape changes and relate them to the required changes in the pressure or velocity distribution. To display the power of the methods, design cases are presented in the subsonic and transonic regimes. A circulation control design case is also presented using one of the methods to further show the robustness of the method.

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8

Ghasemi, Esfahani Ata. "Physics and Control of Flow Over a Thin Airfoil using Nanosecond Pulse DBD Actuators." The Ohio State University, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=osu1503204430451055.

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9

Rinehart, Aidan Walker. "A Characterization of Seal Whisker Morphology and the Effects of Angle of Incidence on Wake Structure." Cleveland State University / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=csu1483991011265196.

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10

Byrd, Alex W. "Fluid-Structure Interaction Simulations of a Flapping Wing Micro Air Vehicle." Wright State University / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=wright1401559891.

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11

Pearl, Jason M. "Two-Dimensional Numerical Study of Micronozzle Geometry." ScholarWorks @ UVM, 2016. http://scholarworks.uvm.edu/graddis/579.

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Supersonic micronozzles operate in the unique viscosupersonic flow regime, characterized by large Mach numbers (M>1) and low Reynolds numbers (Re<1000). Past research has primarily focused on the design and analysis of converging-diverging de Laval nozzles; however, plug (i.e. centerbody) designs also have some promising characteristics that might make them amenable to microscale operation. In this study, the effects of plug geometry on plug micronozzle performance are examined for the Reynolds number range Re = 80-640 using 2D Navier-Stokes-based simulations. Nozzle plugs are shortened to reduce viscous losses via three techniques: one - truncation, two - the use of parabolic contours, and three - a geometric process involving scaling. Shortened nozzle are derived from a full length geometry designed for optimal isentropic performance. Expansion ratio (ε = 3.19 and 6.22) and shortened plug length (%L = 10-100%) are varied for the full Reynolds number range. The performance of plug nozzles is then compared to that of linear-walled nozzles for equal pressure ratios, Reynolds numbers, and expansion ratios. Linear-walled nozzle half-angle is optimized to to ensure plug nozzles are compared against the best-case linear-walled design. Results indicate that the full length plug nozzle delivers poor performance on the microscale, incurring excessive viscous losses. Plug performance is increased by shortening the nozzle plug, with the scaling technique providing the best performance. The benefit derived from reducing plug length depends upon the Reynolds number, with a 1-2% increase for high Reynolds numbers an up to 14% increase at the lowest Reynolds number examined. In comparison to Linear-walled nozzle, plug nozzles deliver superior performance when under-expanded, however, this trend reverses at low pressure ratios when the nozzles become over-expanded.

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12

Bebeau, Robert R. "Simulation of Radiation Flux from Thermal Fluid in Origami Tubes." Scholar Commons, 2018. https://scholarcommons.usf.edu/etd/7666.

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Spacecraft in orbit experience temperature swings close to 240 K as the craft passes from the shadow of the Earth into direct sunlight. To regulate the craft’s internal energy, large radiators eject unwanted energy into space using radiation transfer. The amount of radiation emitted is directly related to the topology of the radiator design. Deformable structures such as those made with origami tessellation patterns offer a mechanism to control the quantity of energy being emitted by varying the radiator shape. Three such patterns, the Waterbomb, Huffman Waterbomb, and Huffman Stars-Triangles, can be folded into tubes. Origami tubes offer greater control and simplicity of design than flat radiators. Using FLUENT, Origami Simulator, and Solidworks to first simulate and then analyze the flow of a thermal fluid through the patterns and the radiation emitted from the created bodies, it was determined that the Waterbomb pattern achieved a 17.6 percent difference in emitted radiation, over a 2 percent change in fold. The Huffman Waterbomb pattern displayed a 42.7 percent difference in emitted radiation over a 20 percent change of fold. The simulations demonstrated both the feasibility and benefits of the origami designed tubes.

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13

Gobal, Koorosh. "High-Fidelity Multidisciplinary Sensitivity Analysis for Coupled Fluid-Solid Interaction Design." Wright State University / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=wright1483614152174005.

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14

Lucarelli, Nicola. "Pressure-Sensitive Paint Measurements and CFD Analysis of Vortex Flow in a Cyclone Separator." Youngstown State University / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=ysu1579623680778155.

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15

Guarendi, Andrew N. "Numerical Investigations of Magnetohydrodynamic Hypersonic Flows." University of Akron / OhioLINK, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=akron1365985409.

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16

Ingraham, Daniel. "External Verification Analysis: A Code-Independent Approach to Verifying Unsteady Partial Differential Equation Solvers." University of Toledo / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1430491745.

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17

Barnes, Caleb J. "Unsteady Physics and Aeroelastic Response of Streamwise Vortex-Surface Interactions." Wright State University / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=wright1431937866.

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18

Miller, Samuel C. "Fluid-Structure Interaction of a Variable Camber Compliant Wing." University of Dayton / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1428575972.

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19

Kiflemariam, Medet. "Development of a CFD Boundary Condition to Simulate a Perforated Surface." Thesis, Umeå universitet, Institutionen för fysik, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:umu:diva-185418.

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In aircraft with jet propulsion engine intakes at supersonic speed, strong pressure waves referred to as shockwaves occur, which may interact with any present boundary layers along the intake surface. The adverse pressure gradients associated with Shock Wave-Boundary Layer Interaction (SWBLI) may cause boundary layer flow separation, which can result in disturbances of the flow that can be harmful to the device or decrease engine performance. A common way in dealing with the adverse effects of SWBLI is through removal of low-momentum flow in the boundary layer, a process referred to as boundary layer bleed. In the process of bleed, the boundary layer is subjected to a pressure difference promoting flow out of the system, through a porous surface, and into a plenum. The porous surfaces used in the mass flow removal process contain orifices in small scales. Thus, in Computational Fluid Dynamics (CFD), creating a mesh resolving both the orifice scales and the bulk flow is a cumbersome task, and the computational cost becomes substantially increased. To this end, several boundary conditions which effectively model the large-scale effects of bleed have been developed. The aim of this study is to implement the Boundary Condition (BC) developed by John W. Slater into M-EDGE, the in-house compressible CFD-solver of SAAB Aeronautics. The bleed boundary condition model is based on a dimensionless surface sonic flow coefficient, which is derived from empirical wind-tunnel measurements of the bleed mass flow. In previous work, the Slater bleed BC has been shown to correlate well with wind-tunnel data. Furthermore, a simple transpiration law formulated by Reynald Bur was implemented in order get familiarized with the M-EDGE Fortran source code. However, this model is expected to yield unsatisfactory results, as reported in previous work in the field. The implemented Slater BC is tested on two different two-dimensional flow cases; flow over a flat plate without SWBLI, and flow including a shock wave generator creating SWBLI. In the flat plate case, simulations were run at Mach numbers 1.27, 1.58, 1.98 and 2.46 over a 6.85cm plate of 19% porosity. In the SWBLI-case, only flow at Mach 2.46 was considered, with a 9.53cm plate of 21% porosity. The Reynolds number range used throughout was 1.39−1.76·10^7/m. Simulations were run at different bleed rates over a structured grid using steady state RANS with the Spalart-Allmaras one-equation turbulence model. The boundary condition performance was assessed by its ability to recreate the sonic flow coefficients on which it is based. Further, the shape of downstream pitot pressure profiles are compared with experimental data. Results from the studies indicate that the implementation manages to recreate the data for the sonic flow coefficient with small error margins. The implementation can be used to simulate porous plates of different dimensions and porosities, even though the bleed model is based on empirical mass flow measurements of a 6.85cmplate of 19% porosity. The implementation is able to predict global bleed effects in the flow field, as indicated by comparisons of pitot pressure profiles at various downstream reference planes, despite differences in reference boundary layer intake profiles. Further, the overall flow field was compared visually with other simulation-studies, indicating that the global Mach distributions of the geometries were in accordance with the reference data. However, pitot profiles should be further studied with better matched intake boundary layer profiles. The main limitation of the boundary condition is that it relies on the wind-tunnel data of the surface sonic flow coefficients for specific bleed plate configurations. Furthermore, the implementation has only been verified to work within specific Mach number range of the underlying empirical measurements. In future work, the generality of the model could be increased by extending the data to other configurations and Mach numbers by conducting new experiments or using other published empirical data.

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20

Sander, Zachary Hugo. "Heat Transfer, Fluid Dynamics, and Autoxidation Studies in the Jet Fuel Thermal Oxidation Tester (JFTOT)." University of Dayton / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1355367856.

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21

Mohan, Arvind Thanam. "Large Eddy Simulationof Separated Flows." The Ohio State University, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=osu1367493651.

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22

Velliyur, Ramachandran Krishna Guha. "An Aeroacoustic Analysis of Wind Turbines." The Ohio State University, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=osu1293650904.

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23

Resor, Michael Irvin. "COMPUTATIONAL INVESTIGATION OF ROTARY ENGINE HOMOGENEOUS CHARGE COMPRESSION IGNITION FEASIBILITY." Wright State University / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=wright1419010366.

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24

Ickes, Jacob. "Improved Helicopter Rotor Performance Prediction through Loose and Tight CFD/CSD Coupling." University of Toledo / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1408476196.

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25

Ning, Zhe. "An Experimental Investigation on the Control of Tip Vortices from Wind Turbine Blade." Wright State University / OhioLINK, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=wright1376658342.

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26

Bilyeu, David L. "A HIGHER-ORDER CONSERVATION ELEMENT SOLUTION ELEMENT METHOD FOR SOLVING HYPERBOLIC DIFFERENTIAL EQUATIONS ON UNSTRUCTURED MESHES." The Ohio State University, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=osu1396877409.

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27

Clifford, Christopher J. "An Investigation of Physics and Control of Flow Passing a NACA 0015 in Fully-Reversed Condition." The Ohio State University, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=osu1440156651.

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28

Kearney-Fischer, Martin A. "The Noise Signature and Production Mechanisms of Excited High Speed Jets." The Ohio State University, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=osu1318961517.

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29

Crawford, Michael R. "A Computational Study of Mixing in Jet Stirred Reactors." University of Akron / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=akron1405328296.

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30

Zhao, Qiuying. "Towards Improvement of Numerical Accuracy for Unstructured Grid Flow Solver." University of Toledo / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1353107603.

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31

Hahn, Casey Bernard. "Design and Validation of the New Jet Facility and Anechoic Chamber." The Ohio State University, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=osu1311877224.

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32

Mazur, Zachary Thomas Lyn. "Calibration and Baseline Flow Surveys of a Reconstructed Boundary-Layer Wind Tunnel." Youngstown State University / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=ysu1597422848793191.

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33

Guzek, Brian John. "Investigation of a Planar Heat Pipe Topology." Case Western Reserve University School of Graduate Studies / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=case1463001160.

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34

Eberhart, Gina M. "Modeling of Ground Effect Benefits for Multi-Rotor Small Unmanned Aerial Systems at Hover." Ohio University / OhioLINK, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=ohiou1502802483367365.

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35

Lanchman, Troy J. "Using CFD to Improve Off-Design Throughflow Analysis." Wright State University / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=wright1559828068015963.

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36

Parkhe, Vineet. "A Parametric Study on Flow Over a Flat Plate with Microblowing." University of Akron / OhioLINK, 2009. http://rave.ohiolink.edu/etdc/view?acc_num=akron1258390482.

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37

Marks, Christopher R. "Surface Stress Sensors for Closed Loop Low Reynolds Number Separation Control." Wright State University / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=wright1309998636.

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38

Knapke, Clint J. "Aerodynamics of Fan Blade Blending." Wright State University / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=wright1567517259599736.

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39

Zhang, Qian. "LAMINAR-TURBULENT TRANSITION FOR ATTACHED AND SEPARATED FLOW." UKnowledge, 2010. http://uknowledge.uky.edu/gradschool_diss/118.

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A major challenge in the design of turbomachinery components for aircraft gas turbine engines is high cycle fatigue failures due to flutter. Of particular concern is the subsonic/transonic stall flutter boundary which occurs at part speed near the stall line. At these operating conditions the incidence angle is large and the relative Mach number is high subsonic or transonic. Viscous effects dominate for high incidence angles. In order to predict the flutter phenomena, accurate calculation of the steady and unsteady aerodynamic loading on the turbomachinery airfoils is necessary. The development of unsteady aerodynamic models to predict the unsteady forces and moments acting on turbomachine airfoils is an area of fundamental research interest. Unsteady Reynolds Averaged Navier-Stokes (RANS) models have been developed to accurately account for viscous effects. For these Reynolds averaged equations turbulence models are needed for the Reynolds stress terms. A transition model is also necessary. The transition onset location is determined by a transition onset model or specified at the suction peak. Usually algebraic, one or two-equation or Reynolds stress turbulence models are used. Since the Reynolds numbers in turbomachinery are large enough to guarantee the flow is turbulent, suitable transition and turbulence models are crucial for accurate prediction of steady and unsteady separated flow. The viscous flow solution of compressor airfoils at off-design conditions is challenging due to flow separation and transition to turbulent flow within separation bubbles. Additional complexity arises when the airfoils are vibrating as is encountered in stall flutter. In this investigation calculations are made of a transonic compressor airfoil in steady flow and with the airfoils oscillating in a pitching motion about the mid-chord at 0° and 10° of chordal incidence angle, and correlated with experiments conducted in the NASA GRC Transonic Flutter Cascade. To model the influence of flow transition on the steady and unsteady aerodynamic flow characteristics, the Solomon, Walker, and Gostelow (SWG) transition model is utilized. The one-equation Spalart-Allmaras model is used to model turbulence. Different transition onset models including fixed onset are implemented and compared for the two incidence angle cases. At each incidence angle, the computational model is compared to the experimental data for the steady flow case and also for pitching oscillation at a reduced frequency of 0.4. The 10° incidence angle case has flow separation over front 40% of the airfoil chord. The operating conditions considered are an inlet Mach number of 0.5 and a Reynolds number of 0.9 Million.

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40

Kerestes, Jared N. "Numerical Investigation of Flow Around a Deformed Vacuum Lighter-Than-Air Vehicle." Wright State University / OhioLINK, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=wright1622235951947085.

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41

Hall, Brenton Taylor. "Using the Non-Uniform Dynamic Mode Decomposition to Reduce the Storage Required for PDE Simulations." The Ohio State University, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=osu1492711382801134.

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42

Jiang, Hua. "Effect of Changes in Flow Geometry, Rotation and High Heat Flux on Fluid Dynamics, Heat Transfer and Oxidation/Deposition of Jet Fuels." University of Dayton / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1300553102.

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43

Yang, Chuanbo. "Wake-Fin Tailoring for Projectile Steering." University of Toledo / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1302200662.

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44

Bork, Carrington E. "Aerodynamic Development of the Buckeye Bullet 3 Electric Landspeed Vehicle." The Ohio State University, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=osu1339688241.

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45

Thamann, Michael. "AERODYNAMICS AND CONTROL OF A DEPLOYABLE WING UAV FOR AUTONOMOUS FLIGHT." UKnowledge, 2012. http://uknowledge.uky.edu/me_etds/18.

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UAV development and usage has increased dramatically in the last 15 years. In this time frame the potential has been realized for deployable UAVs to the extent that a new class of UAV was defined for these systems. Inflatable wing UAVs provide a unique solution for deployable UAVs because they are highly packable (some collapsing to 5-10% of their deployed volume) and have the potential for the incorporation of wing shaping. In this thesis, aerodynamic coefficients and aileron effectiveness were derived from the equations of motion of aircraft as necessary parameters for autonomous flight. A wind tunnel experiment was performed to determine the aerodynamic performance of a bumpy inflatable wing airfoil for comparison with the baseline smooth airfoil from which it was derived. Results showed that the bumpy airfoil has improved aerodynamics over the smooth airfoil at low-Re. The results were also used to create aerodynamic performance curves to supplement results of aerodynamic modeling with a smooth airfoil. A modeling process was then developed to calculate the aileron effectiveness of a wing shaping demonstrator aircraft. Successful autonomous flight tests were then performed with the demonstrator aircraft including in-flight aileron doublets to validate the predicted aileron effectiveness, which matched within 8%.

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46

Belfield, Eric. "Assessment of Asymmetric Flight on Solar UAS." DigitalCommons@CalPoly, 2016. https://digitalcommons.calpoly.edu/theses/1676.

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An investigation was conducted into the feasibility of using an unconventional flight technique, asymmetric flight, to improve overall efficiency of solar aircraft. In this study, asymmetric flight is defined as steady level flight in a non-wings-level state in- tended to improve solar incidence angle. By manipulating aircraft orientation through roll angle, solar energy collection is improved but aerodynamic efficiency is worsened due to the introduction of additional trim drag. A point performance model was devel- oped to investigate the trade-off between improvement in solar energy collection and additional drag associated with asymmetric flight. A mission model with a focus on aircraft orbits was then developed via integration of the point performance model over a set of discrete points. It is shown that there is a non-zero bank angle where optimal net power is achieved for a given aircraft orientation, flight condition, and sun position. The study also shows that there is improvement in overall efficiency over conventional flight for various orbit shapes and winds aloft. This indicates that there is potential value in not only flight path planning, but also in orientation planning for solar aircraft.

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47

Plappally, Anand Krishnan. "Theoretical and Empirical Modeling of Flow, Strength, Leaching and Micro-Structural Characteristics of V Shaped Porous Ceramic Water Filters." The Ohio State University, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=osu1276860054.

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48

Zagnoli, Daniel Anthony. "A Numerical Study of Deposition in a Full Turbine Stage Using Steady and Unsteady Methods." The Ohio State University, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=osu1429796426.

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49

Mendoza, Heimdall. "Effects of a Binary Argon-Helium Shielding Gas Mixture on Ultra-Thin Features Produced by Laser-Powder Bed Fusion Additive Manufacturing." The Ohio State University, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=osu1609443074175487.

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50

Hammer, Patrick Richard. "A Discrete Vortex Method Application to Low Reynolds Number Aerodynamic Flows." University of Dayton / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1311792450.

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