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Dissertations / Theses on the topic 'Aerodynamics. Flight. Aerospace engineering'

Author: Grafiati

Published: 4 June 2021

Last updated: 16 February 2022

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1

Salmons, James Dale. "Developmental flight testing of a half scale unmanned air vehicle." Thesis, Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA240347.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, September 1990.<br>Thesis Advisor(s): Howard, Richard M. Second Reader: Pagenkopf, Eric L. "September 1990." Description based on title screen as viewed on December 18, 2009. DTIC Descriptor(s): Unmanned, Flight Testing, Angles, Steady State, Measurement, Vibration, Maneuverability, Marine Corps, Aircraft, Scale Models, Structural Properties, Tail Assemblies, Theses, Angle Of Attack, Estimates, Fuels, Endurance(General), Flight, Response, Scale, Weight, Airframes, Airspeed, Instrumentation, Recording Systems, Sideslip, Mane

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2

Rhoades, Mark M. "A study of the airwake aerodynamics over the flight deck of an AOR model ship." Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA241008.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, September 1990.<br>Thesis Advisor(s): Healey, J. Val. Second Reader: Schmidt, L. V. "September 1990." Description based on title screen as viewed on December 18, 2009. DTIC Descriptor(s): Velocity, Air Flow, Flight Decks, Shear Properties, Measurement, Position(Location), Ships, Models, Layers, Edges, Boundary Layer, Flow Visualization, Tunnels, Curvature, Smoke, Stationary, Bubbles, Patterns, Helium, Flow, Ship Models, Video Signals, Anemometers, Earth Atmosphere, Deflectors, Photographic Equipment. DTIC Identifier(s): Wake

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3

Eddy, Andito Donisha. "AN INVESTIGATION INTO DELTA WING AERODYNAMICS WITH APPLICATION TO UNMANNED AIRCRAFT IN HIGH ALTITUDE FLIGHT." The Ohio State University, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=osu1532037956695845.

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4

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 w

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5

Hooper, Jack Charles. "Vertical landing flight envelope definition." Thesis, Luleå tekniska universitet, Rymdteknik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-80717.

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This paper will investigate the development of a landing footprint for a re-entry vehicle. Vehicles can re-enter the atmosphere with a range of orientations, velocities and flight path angles. The central question is whether a vehicle with any combination of these states can be brought to an acceptable landing condition at a particular landing site and with a particular landing speed. To aide in this investigation several models must be implemented, including that of the atmosphere, the vehicles, the Earth, and the aerodynamics. A detailed analysis of the aerodynamic model will be treated, and

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6

Sebastian, Thomas Jr. "Methods for the Determination of Aerodynamic Parameters and Trajectory Reconstruction of the Orion Command Module from Scale Model Aeroballistic Flight Data." NCSU, 2008. http://www.lib.ncsu.edu/theses/available/etd-11042008-170009/.

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Determination of aerodynamic coeffcients and stability derivatives is necessary in defning a model of the Orion CEV dynamics. This involves reducing experimental data, which can include acceleration, angular rate, or orientation data. This sort of extraction of dynamics from experimental data is often performed on data gathered from experiments conducted on uninstrumented models at indoor ballistics ranges. The US Army Research Laboratory (ARL) has developed a high-g survivable stand-alone instrumentation package that can transmit in-flight measurements of acceleration, angular rate, and local

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7

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 collecti

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8

Gai, Kuo. "Wing Damage Effect on Dragonfly’s Aerodynamic Performance during Takeoff." Wright State University / OhioLINK, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=wright1367934121.

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9

Jacobsson, David. "Learning to Fly: Upgraded Aerodynamics and Control Surfaces." Thesis, KTH, Flygdynamik, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-299417.

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In recent times the unmanned quadcopter aircraft has been used for a widening range of applications, but for longer distances it still falls short of conventional airplanes in terms of energy usage. There exists hybrid configurations of unmanned aircraft which combine the mobility of quadcopters and the range of fixed-wing aircraft. The transition between the hovering mode and the gliding mode, however, is a complex non-linear control problem. To solve this a recent study applied a neural network as a closed loop controller. This controller was capable of seamless mode transition and could be

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10

Arustei, Adrian. "Development of a System Identification Tool for Subscale Flight Testing." Thesis, Linköpings universitet, Fluida och mekatroniska system, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-157292.

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Aircraft system identification has been widely used to this day in applications like control law design, building simulators or extending flight envelopes. It can also be utilized for determining flight-mechanical characteristics in the preliminary design phase of a flight vehicle. In this thesis, three common time-domain methods were implemented in MATLAB for determining the aerodynamic derivatives of a subscale aircraft. For parameter estimation, the equation-error method is quick, robust and can provide good parameter estimates on its own. The output-error method is computationally intensiv

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11

Peters, Brett. "On Accelerating Road Vehicle Aerodynamics." Thesis, The University of North Carolina at Charlotte, 2018. http://pqdtopen.proquest.com/#viewpdf?dispub=10791882.

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<p> Road vehicle aerodynamics are primarily focused on developing and modeling performance at steady-state conditions, although this does not fully encompass the entire operating envelope. Considerable vehicle acceleration and deceleration occurs during operation, either because of driver input or from transient weather phenomenon such as wind gusting. With this considered, high performance road vehicles experience body acceleration rates well beyond ±1G to navigate courses during efficient transition in and out of corners, accelerating from maximum straight-line speed to manageable cor

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12

Kumar, Manish. "Application of frequency-domain-method to rotorcraft aerodynamics." Related electronic resource: Current Research at SU : database of SU dissertations, recent titles available full text, 2008. http://wwwlib.umi.com/cr/syr/main.

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13

Wahlers, Kristen Erin. "A Design for a High Altitude Flight Test System." MSSTATE, 2006. http://sun.library.msstate.edu/ETD-db/theses/available/etd-04162006-163320/.

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Small UAV?s and flight vehicles in other atmospheres such as Mars are characterized by low Reynolds numbers. Low Reynolds number airfoil testing has been difficult to achieve and there are few centers that can accomplish this task. This study is an effort to develop a flight test system that will enable low Reynolds number tests to be performed with a simple glider design. The concept is to develop a high altitude glider that will be transported to altitudes reaching 100,000 feet or more by a helium filled balloon. At altitude, the glider will be released and will perform flight experiments as

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14

Vestlund, Oscar. "Aerodynamics and Structure of a Large UAV." Thesis, Mälardalens högskola, Akademin för innovation, design och teknik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:mdh:diva-38562.

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This thesis investigates what design of a large UAV performing VTOL using only electrical motors is the most viable in terms of extending its range. Because it uses batteries for power, its powered time is limited, posing the need for a way of extending its flight time. By using a tiltwing design, its vertical flight time is cut at the same time as it will be able to perform as a glider, increasing its range drastically. To achieve the best lift-to-drag ratio, the high-lift F3B RG15-airfoil was chosen, giving the UAV a lift-to-drag ratio of 36,48, and a maximum range per descend glide of appro

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15

Pierre, Sylvain. "Aerodynamics of wings with leading-edge flow separation in supersonic regime." Thesis, McGill University, 1992. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=60716.

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Analytical methods solving for the separated flow over delta wings have been based on the slender-body theory, which applies for wing geometries of small aspect ratio. The slender-body solutions are independent of the Mach number, and therefore, for supersonic flow, cannot appropriately take into account the directional propagation of disturbances. The slender-body model is attractively simple of the pressure distribution and lift prediction, but in the supersonic regime it can lead to large errors when the wing geometry is not very slender with respect to the Mach cone.<br>In the treatment of

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16

Merlet, Pierre Miguel. "Flight Mechanics of an Airship." Thesis, KTH, Flygdynamik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-290178.

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Airships were very popular 90 years ago with, for example, german Zeppelins. Now theyare back for several reasons, like their low energy consumption.But there are also still many problems to deal with like their sensitivity to wind gusts.In addition, the airships need more studies to improve their flight mechanics and sensitivityto the wind.This degree project, done with the French Aerospace Lab ONERA in Lille, studies a specificairship which is 5mlong and 1.7mwide. First, the airship is studied without wind to determineaerodynamic coefficients and added masses. Then, the model is confronted t

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17

Bandte, Oliver. "A probabilistic multi-criteria decision making technique for conceptual and preliminary aerospace systems design." Diss., Georgia Institute of Technology, 2000. http://hdl.handle.net/1853/12503.

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18

Wu, Xiaonan. "Design and Development of Variable Pitch Quadcopter for Long Endurance Flight." Thesis, Oklahoma State University, 2019. http://pqdtopen.proquest.com/#viewpdf?dispub=10813154.

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<p> The variable pitch quadrotor is not a new concept but has been largely ignored in small unmanned aircraft, unlike the fixed pitch quadcopter which is controlled only by changing the RPM of the motors and only has about 30 minutes of total flight time. The variable pitch quadrotor can be controlled either by the change of the motor RPM or rotor blade pitch angle or by the combination of both. This gives the variable pitch quadrotor potential advantages in payload, maneuverability and long endurance flight. This research is focused on the design methodology for a variable pitch quadrotor usi

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19

Falquier, Rene. "Longitudinal Flight Mechanics of Paraglider Systems." Thesis, KTH, Flygdynamik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-261698.

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This project outlines a cost-effective numerical simulation method for the analysis of the longitudinal mechanics of paraglider systems. It is built on static stability methods for the analyses of low subsonic aircraft, non-linear lifting line methods for aerodynamic parameterization, and frequency domain analysis methods derived from system theory. Paragliders possess a glide polar in the range of ≈ 25-60 km.h−1 and display underdamped dynamic responses dominated by a long-period mode. The simulation results for performance and dynamic response are qualitatively valid relative to experimental

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Rossignol, Clémence. "Developing algorithms for Flight Data Monitoring." Thesis, KTH, Flygdynamik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-276464.

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Flight data are recorded on every commercial aircraft to be analysed and therefore improve flight safety. This analysis is done through various algorithms computing new parameters and detecting precise instants of the flight (rotation, take-off, touchdown, etc.). These instants are used to flag events when a safety risk occurred during the flight. High-accuracy in the detection of instants is of prime importance to avoid missed events and flagged false events.<br>Flygdata registreras på alla kommersiella flygplan för att analyseras och därmed förbättra flygsäkerheten. Denna analys görs genom o

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21

Jurta, Daniel S. "Validation of the USNTPS simulator for the advanced flight controls design exercise." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2005. http://library.nps.navy.mil/uhtbin/hyperion/05Dec%5FJurta.pdf.

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22

Germann, Kenneth Paul. "T-6A TEXAN II IN-FLIGHT SIMULATION AND VARIABLE STABILITY SYSTEM DESIGN." MSSTATE, 2009. http://sun.library.msstate.edu/ETD-db/theses/available/etd-12162009-091123/.

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In-flight variable stability aircraft and in-flight simulation are described. The uses of these vehicles and the associated requirements are described. Several forms of control architecture are identified for use in a T-6A in-flight simulator. A non-linear model of the T-6A Texan II is developed for use in MATLAB/SIMULINK®. This model is used to design a feedforward response-feedback controller, based on simplified dynamic inversion. This controller is shown to exercise precise control over the T-6A host aircraft dynamics. This architecture is then used to demonstrate simulation of the A-4 and

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23

Fagin, Maxwell H. "Payload mass improvements of supersonic retropropulsive flight for human class missions to Mars." Thesis, Purdue University, 2016. http://pqdtopen.proquest.com/#viewpdf?dispub=10046736.

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<p> Supersonic retropropulsion (SRP) is the use of retrorockets to decelerate during atmospheric flight while the vehicle is still traveling in the supersonic/hypersonic flight regime. In the context of Mars exploration, <i>subsonic</i> retropropulsion has a robust flight heritage for terminal landing guidance and control, but all <i>supersonic</i> deceleration has, to date, been performed by non-propulsive (i.e. purely aerodynamic) methods, such as aeroshells and parachutes.</p><p> Extending the use of retropropulsion from the subsonic to the supersonic regime has been identified as an enab

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Munther, Peter Antoine. "Design study of a high altitude morphing UAV with analysis of low Reynolds number parawing aerodynamics." The Ohio State University, 2006. http://rave.ohiolink.edu/etdc/view?acc_num=osu1413455228.

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25

Lee, Daniel M. "Development of a 1/7th scale fighter UAV for flight research." Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA240703.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, September 1990.<br>Thesis Advisor(s): Howard, Richard M. Second Reader: Pagenkopf, Eric L. "September 1990." Description based on title screen as viewed on March 18, 2010. DTIC Identifier(s): Remotely Piloted Vehicles, Flight Maneuvers, Parachute Descents, UAV (Unmanned Air Vehicles), Supermaneuverability, Scale Models, Remote Control, Research Aircraft, Radio Transmission, High Angle of Attack, Aircraft Models, Naval Aircraft, Jet Fighters, Recovery, Theses. Author(s) subject terms:UAV, Supermaneuverability, Emergency Recov

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26

Parker, Colin M. "An Investigation into the Aerodynamics Surrounding Vertical-Axis Wind Turbines." Thesis, The George Washington University, 2018. http://pqdtopen.proquest.com/#viewpdf?dispub=10687173.

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<p> The flow surrounding a scaled model vertical-axis wind turbine (VAWT) at realistic operating conditions was studied. The model closely matches geometric and dynamic properties—tip-speed ratio and Reynolds number—of a full-size turbine. The flowfield is measured using particle imaging velocimetry (PIV) in the mid-plane upstream, around, and after (up to 4 turbine diameters downstream) the turbine, as well as a vertical plane behind the turbine. Ensemble-averaged results revealed an asymmetric wake behind the turbine, regardless of tip-speed ratio, with a larger velocity deficit

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27

Sveinbjarnarson, Unnar Már. "Anomaly Detection based on Boeing 757-200 Flight Data." Thesis, KTH, Flygdynamik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-239042.

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This paper deals with anomaly detection from collected flight data for a Boeing 757-200currently in use by Icelandair. Previous work on anomaly detection using generated datahas been shown to give good results using multiple linear regression models. Using a similarapproach the paper addresses how the amount of data effects the models ability to detectanomalies. Simple regression approach is compared to a quadratic one and practical use ofmaintenance data in this context is explored. Finally different model variations are investigatedto attempt further root cause analysis of faults.

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Sobron, Alejandro. "On Subscale Flight Testing : Applications in Aircraft Conceptual Design." Licentiate thesis, Linköpings universitet, Fluida och mekatroniska system, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-152488.

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Downscaled physical models, also referred to as subscale models, have played an essential role in the investigation of the complex physics of flight until the recent disruption of numerical simulation. Despite the fact that improvements in computational methods are slowly pushing experimental techniques towards a secondary role as verification or calibration tools, real-world testing of physical prototypes still provides an unmatched confidence. Physical models are very effective at revealing issues that are sometimes not correctly identified in the virtual domain, and hence can be a valuable

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Pothier, Valentin. "Bending modes analysis in atmospheric flight for heavy launcher." Thesis, KTH, Flygdynamik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-265615.

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This report presents the bending modes study conducted on a heavy launcher. The controller of the launcher takes as inputs the attitude and attitude rate measurements given by the Inertial Measurement Unit (IMU). Since the bending modes generate measurement errors at the IMU location, the study of deformations due to these bending modes is critical to assess the stability of the launcher during the atmospheric flight phase. The goal of this master thesis project is to detect and then select the most excitable bending modes among the large number of modes provided by a detailed structural analy

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30

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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31

FU, YONGQIANG. "Aerodynamics and Combustion of Axial Swirlers." University of Cincinnati / OhioLINK, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1204551619.

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32

Zeppetelli, Danial. "Computational fluid dynamics icing analysis: a predictive approach to in-flight icing risk management and aircraft certification." Thesis, McGill University, 2011. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=104598.

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In-flight icing is a hazard that continues to afflict the aviation industry, despite all the research and efforts to mitigate the risks. The recurrence of these types of accidents has given renewed impetus to the development of advanced analytical predictive tools to study both the accretion of ice on aircraft components in flight, and the aerodynamic consequences of such ice accumulations. In this work, an in-depth analysis of the occurrence of in-flight icing accidents and incidents was conducted to identify high-risk flight conditions. To investigate these conditions more thoroughly, a comp

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33

Yu, Qiuli. "AIRCRAFT FLIGHT DATA PROCESSING AND PARAMETER IDENTIFICATION WITH ITERATIVE EXTENDED KALMAN FILTER/SMOOTHER AND TWO-STEP ESTIMATOR." MSSTATE, 2001. http://sun.library.msstate.edu/ETD-db/theses/available/etd-11262001-105646/.

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Aircraft flight test data are processed by optimal estimation programs to estimate the aircraft state trajectory (3 DOF) and to identify the unknown parameters, including constant biases and scale factor of the measurement instrumentation system. The methods applied in processing aircraft flight test data are the iterative extended Kalman filter/smoother and fixed-point smoother (IEKFSFPS) method and the two-step estimator (TSE) method. The models of an aircraft flight dynamic system and measurement instrumentation system are established. The principles of IEKFSFPS and TSE methods are derived

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34

Johansson, Emil. "Implications of Designing Unstable Aircraft from a Flight Control Perspective." Thesis, KTH, Flygdynamik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-265783.

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Designing a flight control system for an aircraft is a multifaceted task which has to take many requirements and constrints into account. Being able to quickly evaluate the feasibility of achieving design targets in terms of – for example – maneuvering capability and stability mar-gins is valuable when faced with the task of designing a flight control system for a new aircraft or aircraft configuration. This thesis presents methods to quickly assess the maneuverability capability of an aircraft with certain dynamics and control servo constraints by inverting the aircraft dynamics. Limitations

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Thompson, Ernest. "Incorporation of Computational Fluid Dynamics into Flight Vehicle Preliminary Design." University of Dayton / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1335270317.

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36

Blanchette, Bryan M. "The design and construction of a shiplaunched VTOL unmanned air vehicle." Thesis, Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA238053.

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Thesis (M.S. in Engineering Science)--Naval Postgraduate School, June 1990.<br>Thesis Advisor(s): Howard, Richard M. Second Reader:Pagenkopf, Eric L. "June 1990." Description based on title screen as viewed on October 19, 2009. DTIC Descriptor(s): Remotely piloted vehicles, vertical takeoff aircraft, ducted fans, velocity, flight testing, measurement, recovery, aircraft, hazards, demonstrations, fabrication, cycles, flight, vertical orientation, test vehicles, unmanned, safety, takeoff, shipboard, engines, reinforced plastics, propeller blades, propellers, static tests, tilt, thrust, horizonta

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Green, William Edward Oh Paul Yu. "A multimodal micro air vehicle for autonomous flight in near-earth environments /." Philadelphia, Pa. : Drexel University, 2007. http://hdl.handle.net/1860/1764.

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38

Bornemeier, Matthew T. "A Pragmatic Analysis of Helicopter Response to Turbulent Air Wake in a Shipboard Flight Deck Environment." Thesis, The George Washington University, 2015. http://pqdtopen.proquest.com/#viewpdf?dispub=1595329.

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<p> An experiment consists of a remote-controlled T-REX 600E Pro helicopter piloted above an underway 108-foot Patrol Craft’s (YP) flight deck to analyze the effect of <i>Re<sub>H</sub></i> ≈ 3.4×10<sup> 5</sup> turbulent ship air wake on helicopter angular motion. The motion is measured by an inertial measurement unit (IMU) sensor mounted on the helicopter transmitting variably-spaced data in a 3-D Cartesian reference frame. Data is collected with the helicopter in locations above the flight deck which closely match actual takeoff/landing positions of US Navy H-60 helicopters a

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Gao, Yang. "Advances in low-thrust trajectory optimization and flight mechanics /." free to MU campus, to others for purchase, 2003. http://wwwlib.umi.com/cr/mo/fullcit?p3115547.

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40

Bayati, Arastoo, and Peter Reinders. "Conceptual Design of a Small Size Unmanned Air Vehicle : Part B: Flight Performance and Flight Mechanics." Thesis, KTH, Skolan för teknikvetenskap (SCI), 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-297889.

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This report summarizes the task of conceptually designing an UAV suited for agricultural observation of Swedish farmland. The design of the UAV was divided into two parts. This report focuses on the flight mechanics, performance analysis, and cost analysis of the UAV, whereas the other part centers around the aerodynamic performance. Therefore, some elements, such as the wing selection, will not be subject to discussion in this report. A set of different requirements were posed, such as having a flight time longer than two hours, being able to between 5-10 m/s, able to perform vertical take-of

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Palakurthi, Nithin Kumar. "Aerodynamics of Particle Detachment from Surfaces: A Numerical Study." University of Cincinnati / OhioLINK, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1511867161850956.

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42

Gunaydinoglu, Erkan. "Low Reynolds Number Aerodynamics Of Flapping Airfoils In Hover And Forward Flight." Master's thesis, METU, 2010. http://etd.lib.metu.edu.tr/upload/12612397/index.pdf.

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The scope of the thesis is to numerically investigate the aerodynamics of flapping airfoils in hover and forward flight. The flowfields around flapping airfoils are computed by solving the governing equations on moving and/or deforming grids. The effects of Reynolds number, reduced frequency and airfoil geometry on unsteady aerodynamics of flapping airfoils undergoing pure plunge and combined pitch-plunge motions in forward flight are investigated. It is observed that dynamic stall of the airfoil is the main mechanism of lift augmentation for both motions at all Reynolds numbers ranging from 1

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CAI, JUN. "AERODYNAMICS OF LEAN DIRECT INJECTION COMBUSTOR WITH MULTI-SWIRLER ARRAYS." University of Cincinnati / OhioLINK, 2006. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1148233034.

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44

Lugo, Rafael Andres. "Statistical Entry, Descent, and Landing Flight Reconstruction with Flush Air Data System Observations using Inertial Navigation and Monte Carlo Techniques." Thesis, North Carolina State University, 2014. http://pqdtopen.proquest.com/#viewpdf?dispub=3584008.

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<p> A method is introduced to consider flush air data system (FADS) pressures using a technique based on inertial navigation to reconstruct the trajectory of an atmospheric entry vehicle. The approach augments the recently-developed Inertial Navigation Statistical Trajectory and Atmosphere Reconstruction (INSTAR), which is an extension of inertial navigation that provides statistical uncertainties by utilizing Monte Carlo dispersion techniques and is an alternative to traditional statistical approaches to entry, descent, and landing trajectory and atmosphere reconstruction.</p><p> The method

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Harris, Bryan William. "Fiber Optics for Flight Control Systems." University of Dayton / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1418340523.

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Guzman, Carmen Theresa 1966. "Ratioing radiometer, solar diffuser system for in-flight calibration of multispectral satellite sensors." Thesis, The University of Arizona, 1991. http://hdl.handle.net/10150/277975.

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One promising way to calibrate a satellite sensor in flight is to place a sun-illuminated white diffuser panel in front of it. However, even if the panel is only deployed for brief periods, it may degrade in the space environment. A ratioing radiometer to monitor the panel changes is described and an error analysis associated with the use of the radiometer is presented. The procedures used to test the optical properties of different candidate panel materials are described. Results of spectral directional-hemispherical reflectance, bidirectional reflectance, polarization and depolarization meas

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47

Janiszewska, Jolanta M. "Three dimensional aerodynamics of a simple wing in oscillation including effects of vortex generators." Columbus, Ohio : Ohio State University, 2004. http://rave.ohiolink.edu/etdc/view?acc%5Fnum=osu1086190848.

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Thesis (Ph. D.)--Ohio State University, 2004.<br>Title from first page of PDF file. Document formatted into pages; contains xvii, 147 p.; also includes graphics (some col.). Includes abstract and vita. Advisor: Gerald Gregorek, Aeronautical and Astronautical Engineering Graduate Program. Includes bibliographical references (p. 119-122).

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48

Connolly, Joseph. "Aero-Propulso-Elastic Analysis of a Supersonic Transport." The Ohio State University, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=osu1543337967878799.

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Krumanaker, Matthew Lee. "Aerodynamics and Heat Transfer for a Modern Stage and One-Half Turbine." The Ohio State University, 2003. http://rave.ohiolink.edu/etdc/view?acc_num=osu1039538775.

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Sharpe, Jacob Andrew. "3D CFD Investigation of Low Pressure Turbine Aerodynamics." Wright State University / OhioLINK, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=wright1495872867696744.

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