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Dissertations / Theses on the topic 'Aircraft wake'

Author: Grafiati

Published: 7 July 2024

Last updated: 31 July 2025

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1

Stephan, Anton. "Wake vortices of landing aircraft." Diss., Ludwig-Maximilians-Universität München, 2014. http://nbn-resolving.de/urn:nbn:de:bvb:19-167566.

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2

Bertényi, Tamás. "Merger of aircraft wake vortices." Thesis, University of Cambridge, 2002. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.620288.

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3

Rodenhiser, Rebecca J. "An Ultrasonic Method for Aircraft Wake Vortex Detection." Digital WPI, 2005. https://digitalcommons.wpi.edu/etd-theses/1004.

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"This thesis documents the experimental proof of concept study for an ultrasonic method of wake vortex detection. A new acoustic technique is utilized to measure the circulation produced in the wake of lift-generating aircraft. Ultrasonic signals are transmitted in a path around the wake vortex, and are used to determine the average in-line velocity component along the acoustic path. It is shown herein that this velocity component is directly proportional to the net circulation value within the acoustic path. This is the first study to take this methodology and implement it in a realistic airp

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4

Rodenhiser, Rebecca J. "An ultrasonic method for aircraft wake vortex detection." Link to electronic thesis, 2004. http://www.wpi.edu/Pubs/ETD/Available/etd-083105-160931/.

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5

Marles, David. "Effect of an axial jet aircraft wake vortices." Thesis, University of Bath, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.488899.

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An experimental study has been performed to evaluate the effect of a cold axial jet on a variety of typical aircraft wake vortex systems in the near-field. This research attempted to alleviate the vortex hazard imposed on trailing aircraft, which is especially important in the crowded skies around airfields.

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6

Andronache, Constantin. "A study of aerosol interactions in aircraft wake and background atmosphere." Diss., Georgia Institute of Technology, 1996. http://hdl.handle.net/1853/26008.

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7

Stephan, Anton [Verfasser], and George C. [Akademischer Betreuer] Craig. "Wake vortices of landing aircraft / Anton Stephan. Betreuer: George C. Craig." München : Universitätsbibliothek der Ludwig-Maximilians-Universität, 2014. http://d-nb.info/1049393155/34.

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8

Roa, Perez Julio Alberto. "Development of Aircraft Wake Vortex Dynamic Separations Using Computer Simulation and Modeling." Diss., Virginia Tech, 2018. http://hdl.handle.net/10919/96199.

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This dissertation presents a research effort to evaluate wake vortex mitigation procedures and technologies in order to decrease aircraft separations, which could result in a runway capacity increase. Aircraft separation is a major obstacle to increasing the operational efficiency of the final approach segment and the runway. An aircraft in motion creates an invisible movement of air called wake turbulence, which has been shown to be dangerous to aircraft that encounter it. To avoid this danger, aircraft separations were developed in the 1970s, that allows time for wake to be dissipated and

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9

Craig, Margaret Elizabeth. "Trailing-Edge Blowing of Model Fan Blades for Wake Management." Thesis, Virginia Tech, 2005. http://hdl.handle.net/10919/30886.

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Model fan blades designed to implement the wake management technique of trailing-edge blowing were tested in a linear cascade configuration. Measurements were made on two sets of blowing blades installed in the Virginia Tech low-speed linear cascade wind tunnel. The simple blowing blades were identical to the baseline GE Rotor B blades, aside from a slight difference in trailing-edge thickness, a set of internal flow passages, and a blowing slot just upstream of the trailing-edge on the suction side of the blade. The Kuethe vane blades were also slightly thicker at the trailing-edge, and ha

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10

Schroeder, Nataliya. "Analysis of Potential Wake Turbulence Encounters in Current and NextGen Flight Operations." Thesis, Virginia Tech, 2011. http://hdl.handle.net/10919/40924.

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Wake vortices pose a threat to a following aircraft, because they can induce a roll and compromise the safety of everyone on board. Caused by a difference in pressure between the upper and the lower part of the wings, these invisible flows of air are a major hazard and have to be avoided by separating the aircraft at considerable distances. One of the known constraints in airport capacity for both departure and arrival operations is the large headway resulting from the wake spacing separation criteria. Reducing wake vortex separations to a safe level between successive aircraft can increase ca

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11

Hall, Jacob Thomas. "Modeling and analysis of a maneuvering aircraft and cable towed body with wake effects." Thesis, Massachusetts Institute of Technology, 2010. http://hdl.handle.net/1721.1/59671.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2010.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (p. 105-107).<br>This thesis report covers the analysis and modeling of a cable towed endbody that incorporates an aircraft, wake effects, a towline, and a tow body. The aircraft is modeled as a generic tactical aircraft which is able to conduct maneuvers. The towline is treated as an elastic cable that connects the aircraft and endbody while also being affected by the aircraft wake. The endbody is treated as a simple

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12

Myers, Theodore J. "Determination of Bragg Scatter in an Aircraft Generated Wake Vortex System for Radar Detection." Diss., Virginia Tech, 1997. http://hdl.handle.net/10919/30719.

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Remote detection and tracking of wingtip generated wake vortices is important for hazard avoidance especially near airports. Aircraft that fly through these hazardous vortices experience sudden induced roll. Experiments have demonstrated that there is sufficient radar cross section for remote detection at frequencies ranging from VHF to C band (100 MHz to 5 GHz). The mechanism that yields this radar cross section is Bragg scattering from the index of refraction variations due to the atmospheric water vapor and potential temperature fields being mixed by the wake vortex system. Refractive i

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13

Fonti, Elio. "Measurements of aircraft wake vortices in ground proximity within an atmospheric boundary layer wind tunnel." Thesis, Cranfield University, 2010. http://dspace.lib.cranfield.ac.uk/handle/1826/5635.

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The vortex wake characteristics of aircraft during landing and take-off are of interest in connection with both the safety of following aircraft penetrating the vortex and the dispersion of engine exhaust plumes. A series of measurements were carried out in an Atmospheric Boundary Layer Wind Tunnel (ABLWT) to identify and characterise both the mean and turbulent flow field of a pair of wake vortices in ground proximity. Cont/d.

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14

Trupka, Andrew Tristan. "Tracer gas mapping of beverage cart wake in a twin aisle aircraft cabin simulation chamber." Thesis, Kansas State University, 2011. http://hdl.handle.net/2097/8853.

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Master of Science<br>Department of Mechanical and Nuclear Engineering<br>Mohammad H. Hosni<br>Byron W. Jones<br>In 2010, over 786 million passengers flew on commercial flights in the United States according to the Bureau of Transportation Statistics (2011). With the average flight length over 1300 miles for domestic flights, this amounts to billions of hours spent aboard airliners by passengers each year. During these flights, diseases and other harmful contaminates, some malicious, can spread throughout aircraft cabins, harming passengers. Aircraft ventilation systems are designed to remov

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15

Mauermann, Tobias [Verfasser], and L. [Akademischer Betreuer] Tichy. "Flexible Aircraft Modelling for Flight Loads Analysis of Wake Vortex Encounters / Tobias Mauermann ; Betreuer: L. Tichy." Braunschweig : Technische Universität Braunschweig, 2010. http://d-nb.info/1175825352/34.

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16

Frink, William D. Jr. "Hot-wire surveys in the vortex wake downstream of a three-percent fighter aircraft model at high angles of attack." Thesis, Monterey, California: Naval Postgraduate School, 1990. http://hdl.handle.net/10945/27586.

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Approved for public release; distribution is unlimited.<br>A low-speed wind tunnel investigation was conducted to examine the vortex wake downstream of a three-percent scale model of the YF-17 lightweight fighter prototype at high angles of attack. The study was in support of NASA ames Research Center's wind tunnel investigation of a full scale FA-18 as part of NASA's High Alpha Technology Program. Smoke flow visualization was used to locate the downstream vortex wake. Hot-wire surveys were taken through the vortex at two stations; one directly aft of the model and the other at a station three

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17

Frink, William D. "Hot-wire surveys in the vortex wake downstream of a three-percent fighter aircraft model at high angles of attack." Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA241869.

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Thesis (M.S. in Engineering Science)--Naval Postgraduate School, December 1990.<br>Thesis Advisor(s): Hebbar, Sheshagiri K. ; Platzer, Max F. "December 1990." Description based on title screen as viewed on March 31, 2010. DTIC Identifier(s): Trailling Vortices, Wake, Trubulent Flow, Jet Fighters, High Alpha (High Angle of Attack), Vortex Wake, Angle of Attack, Extendable Structures, Leading Edges, Fences, Lex Fences, Wind Tunnel Models, F-17 Aircraft, F/A-18 Aircraft, Wind Tunnel Tests, Hot Wire Anemometers, Theses. Author(s) subject terms: High Angle-of-Attack Aerodynamics, Hot-Wire Measureme

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18

Geiger, Derek Henry. "Comparative Analysis of Serrated Trailing Edge Designs on Idealized Aircraft Engine Fan Blades for Noise Reduction." Thesis, Virginia Tech, 2004. http://hdl.handle.net/10919/40542.

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The effects of serrated trailing edge designs, designed for noise reduction, on the flow-field downstream of an idealized aircraft engine fan blade row were investigated in detail. The measurements were performed in the Virginia Tech low speed linear cascade tunnel on one set of baseline GE-Rotor-B blades and four sets of GE-Rotor-B blades with serrated trailing edges. The four serrated blade sets consisted of two different serration sizes (1.27 cm and 2.54 cm) and for each different serration size a second set of blades with added trailing edge camber. The cascade row consisted of 8 GE-Rotor-

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19

Mirmohammadsadeghi, Navid. "Improvements to Airport Systems Capacity and Efficiency Using Computer Models and Tools." Thesis, Virginia Tech, 2017. http://hdl.handle.net/10919/84301.

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This thesis presents two aspects of air transportation systems, capacity and efficiency. The first study improved a runway capacity simulation model for estimating the capacity of airports under various conditions. The main contribution of this study was to develop a simulation model which is able to analyze different airports with individual aircraft types. Many air traffic regulations were added to the simulation model to give more realistic results to the potential users of the model. Analysis of different separation systems between aircraft pairs show that the capacity of airports can impr

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20

Saulgeot, Pierre. "Contributions à la compréhension de la formation et de l'atténuation possible des traînées de condensation de l'aviation." Electronic Thesis or Diss., Institut polytechnique de Paris, 2023. http://www.theses.fr/2023IPPAX143.

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Les traînées de condensation sont des nuages de glace qui se forment dans le sillage des avions. Leur étude, y compris leur impact météorologique, est rendue difficile par la nécessité de comprendre de nombreuses échelles spatiales et temporelles, depuis la sortie du moteur jusqu'aux cirrus induits dont l'extension peut atteindre plusieurs centaines de kilomètres carrés. Cette thèse s'intéresse à l'influence des tourbillons de sillage, aussi appelés tourbillons marginaux, sur la distribution du panache moteur et la condensation de la vapeur d'eau en glace, de leur enroulement à leur déstabilis

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21

Brundin, Desirée. "An Experimental Study of the High-Lift System and Wing-Body Junction Wake Flow Interference of the NASA Common Research Model." Thesis, KTH, Optimeringslära och systemteori, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-209242.

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This thesis investigates the turbulent flow in the wake of the wing-body junction of the NASA Common Research Model to further reveal its complex vortical structure and to contribute to the reference database used for Computational Fluid Dynamics validation activities. Compressible flows near two wall-boundary layers occurs not only at the wing-body junction but at every control surface of an airplane, therefore increased knowledge about this complex flow structure could potentially improve the estimates of drag performance and control surface efficiency, primarily for minimizing the environme

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22

Jugier, Rémi. "Stabilité bidimensionnelle de modèles de sillage d’aéronefs." Thesis, Toulouse, ISAE, 2016. http://www.theses.fr/2016ESAE0021/document.

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Le contrôle des tourbillons de sillages d'aéronefs permet de réduire leur dangerosité et d'augmenter par conséquent le débit de décollages et d'atterrissages dans les aéroports. Ce contrôle permettrait également d'agir sur la formation des rainées de condensation et des cirrus artificiels en haute atmosphère dans le but de réduire le forçage radiatif terrestre causé par l'aviation. Brion (2014) ont montré par analyse de stabilité modale que le dipôle de Lamb-Chaplygin, souvent utilisé comme un modèle représentatif des tourbillons de sillage en champ lointain, est bidimensionnellement instable

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23

Bardell, N. S. "Wave propagation in periodically stiffened plates and shells." Thesis, University of Southampton, 1990. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.256281.

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24

Shen, G.-C. "The interaction between a plane shock wave and a cylindrical afterbody." Thesis, University of Hertfordshire, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.483961.

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25

Yeung, Chong Pui. "A study of three-dimensional interaction of wakes and boundary-layers." Thesis, University of Cambridge, 1993. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.319566.

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26

Materano, Blanco Gilberto Ignacio. "Numerical modelling of pressure rise combustion for reducing emissions of future civil aircraft." Thesis, Cranfield University, 2014. http://dspace.lib.cranfield.ac.uk/handle/1826/9259.

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This work assesses the feasibility of designing and implementing the wave rotor (WR), the pulse detonation engine (PDE) and the internal combustion wave rotor (ICWR) as part of novel Brayton cycles able to reduce emissions of future aircraft. The design and evaluation processes are performed using the simplified analytical solution of the devices as well as 1D-CFD models. A code based on the finite volume method is built to predict the position and dimensions of the slots for the WR and ICWR. The mass and momentum equations are coupled through a modified SIMPLE algorithm to model compressible

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27

Menday, Roger. "The forced vibration of a partially delaminated beam." Thesis, Loughborough University, 1999. https://dspace.lboro.ac.uk/2134/27082.

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The forced vibration of a partially delaminated structure such as an aircraft wing can result in catastrophic crack growth. In order to look at the underlying mechanism of the dynamics and failure of the material, a simplified model of a cantilever beam with a single delamination at its free end is considered. We investigate a number of aspects of this system, using mathematical models to gain insight into its behaviour.

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28

Kural, Aleksander. "Ultrasonic lamb wave energy transmission system for aircraft structural health monitoring applications." Thesis, Cardiff University, 2013. http://orca.cf.ac.uk/58395/.

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In this project an investigation of a wireless power transmission method utilising ultrasonic Lamb waves travelling along plates was performed. To the author’s knowledge, this is the first time such a system was investigated. The primary application for this method is the supply of power to wireless structural health monitoring (SHM) sensor nodes located in remote areas of the aircraft structure. A vibration generator is placed in a location where electricity supply is readily available. Ultrasonic waves generated by this device travel through the aircraft structure to a receiver in a remote w

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29

Lambert, Luke. "Efficient probabilistic structural response prediction for aircraft turbulence and offshore wave loading." Thesis, University of Liverpool, 2015. http://livrepository.liverpool.ac.uk/2010819/.

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This thesis takes an interdisciplinary approach to the problem of the aleatory uncertainty manifest in the design of engineering structures that are subject to random loading, with specific application to continuous gust loading on aircraft and wave loading on offshore structures. The main focus is on aircraft gust loading because this is the area in which more significant progress is made. A review of the literature on gust loading is carried out to evaluate the sufficiency of existing methods and the possibility of a unified certification model is discussed. In order to obtain reliable proba

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30

Huang, Haidong. "Optimal design of a flying-wing aircraft inner wing structure configuration." Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7439.

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Flying-wing aircraft are considered to have great advantages and potentials in aerodynamic performance and weight saving. However, they also have many challenges in design. One of the biggest challenges is the structural design of the inner wing (fuselage). Unlike the conventional fuselage of a tube configuration, the flying-wing aircraft inner wing cross section is limited to a noncircular shape, which is not structurally efficient to resist the internal pressure load. In order to solve this problem, a number of configurations have been proposed by other designers such as Multi Bubble Fuselag

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31

DeLaurentis, Daniel A. "A probabilistic approach to aircraft design emphasizing stability and control uncertainties." Diss., Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/12948.

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32

Ramasamy, Thaiyal Naayagi. "Bidirectional DC-DC converter for aircraft electric energy storage systems." Thesis, University of Manchester, 2010. https://www.research.manchester.ac.uk/portal/en/theses/bidirectional-dcdc-converter-for-aircraft-electric-energy-storage-systems(34423ae1-ebfb-48bd-a66d-fd03b45615e7).html.

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Future aircraft are likely to employ electrically powered actuators for adjusting flight control surfaces, and other high power transient loads. To meet the peak power demands of aircraft electric loads and to absorb regenerated power, an ultracapacitor-based energy storage system is examined in which a bidirectional dual active bridge DC-DC converter is used. This Thesis deals with the analysis, design, development and performance evaluation of the dual active bridge (DAB) converter, which can act as an interface between the ultracapacitor energy storage bank and the aircraft electrical power

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33

Lock, Wai Lek Willy. "Effects of radio wave propagation in urbanized areas on UAV-GCS command and control." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Dec%5FLock.pdf.

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Thesis (M.S. in Electrical Engineering)--Naval Postgraduate School, December 2003.<br>Thesis advisor(s): David C. Jenn, Jeffrey B. Knorr. Includes bibliographical references (p. 85-87). Also available online.

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34

Plumley, Ryan W. "Conceptual Assessment of an Oblique Flying Wing Aircraft Including Control and Trim Characteristics." Thesis, Virginia Tech, 2008. http://hdl.handle.net/10919/31417.

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A method was developed to assist with the understanding of a unique configuration and investigate some of its stability and control attributes. Oblique wing aircraft concepts are a design option that is well understood, but has yet to be used in a production aircraft. Risk involved in choosing such a design can be averted through additional knowledge early in the concept evaluation phase. Analysis tools commonly used in early conceptual level analysis were evaluated for applicability to a non-standard aircraft design such as an oblique flying wing. Many tools used in early analyses make assum

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35

Rosette, Keith Andrew. "Investigation of a compact acoustic source array for the active control of aircraft engine fan noise." Thesis, This resource online, 1994. http://scholar.lib.vt.edu/theses/available/etd-12302008-063020/.

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36

Bramberger, Martina [Verfasser], and Markus [Akademischer Betreuer] Rapp. "Mountain wave impact on flight conditions of high-flying aircraft / Martina Bramberger ; Betreuer: Markus Rapp." München : Universitätsbibliothek der Ludwig-Maximilians-Universität, 2019. http://d-nb.info/1188564285/34.

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37

Waddington, Michael Jon. "Development of an Interactive Wave Drag Capability for the OpenVSP Parametric Geometry Tool." DigitalCommons@CalPoly, 2015. https://digitalcommons.calpoly.edu/theses/1435.

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Minimizing wave drag is critical to successful and efficient transonic and supersonic flight. Area-ruling is the process of managing the cross-sectional area of an aircraft to lessen the wave drag experienced in flight. Effectively calculating the necessary areas for a given aircraft can be difficult, and existing tools for conducting a wave drag analysis often carry limitations in both functionality and availability. In this work, the author utilized an existing parametric geometry tool named OpenVSP to create an interactive design tool for approximating zero-lift wave drag. Here, the wave dr

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38

Borgoltz, Aurelien. "Modifications of Coherent Structures in Fan Blade Wakes for Broadband Noise Reduction." Diss., Virginia Tech, 2007. http://hdl.handle.net/10919/29619.

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The effects of trailing edge flow control on the wakes of a linear cascade of idealized fan blades was investigated experiments with a view to the likely effects on broadband aircraft engine interaction noise. Single and three-component hotwire velocity measurements were made downstream of the cascade for a chord Reynolds number of 390,000 and a Mach number of 0.07. Measurements of the two-point velocity correlation were used extensively to evaluate the impact of various flow control strategies on the organization of the coherent structures of the wakes and their potential to generate noise.

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39

Pundarika, G. "Experimental And Theoretical Studies On Jet Acoustics." Thesis, Indian Institute of Science, 2001. https://etd.iisc.ac.in/handle/2005/250.

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A systematic research on aeroacoustics conducted around the world for the last few decades has revealed various inherent characteristics of the jet noise radiation. However, a lot more needs to be done for the theoretical as well as experimental predictions of various jet noise features based on actual flow details. The work reported in the present thesis is an attempt in this direction. A critical study of existing literature on jet noise shows that none of the general wave equations lends itself easily for predictions of all the jet noise features. It is shown that while LighthilPs classi

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Pundarika, G. "Experimental And Theoretical Studies On Jet Acoustics." Thesis, Indian Institute of Science, 2001. http://hdl.handle.net/2005/250.

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A systematic research on aeroacoustics conducted around the world for the last few decades has revealed various inherent characteristics of the jet noise radiation. However, a lot more needs to be done for the theoretical as well as experimental predictions of various jet noise features based on actual flow details. The work reported in the present thesis is an attempt in this direction. A critical study of existing literature on jet noise shows that none of the general wave equations lends itself easily for predictions of all the jet noise features. It is shown that while LighthilPs classica

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41

Poh, Seng Cheong Telly. "Simulations of diversity techniques for urban UAV data links." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2004. http://library.nps.navy.mil/uhtbin/hyperion/04Dec%5FPoh.pdf.

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42

Judt, Falko. "Convectively-Generated Potential Vorticity in Rainbands and Secondary Eyewall Formation in Hurricanes." Scholarly Repository, 2009. http://scholarlyrepository.miami.edu/oa_theses/214.

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Concentric eyewall formation and eyewall replacement cycles are intrinsic processes that determine the intensity of a tropical cyclone, as opposed to purely environmental factors such as wind shear or the ocean heat content. Although extensive research has been done in this area, there is not a single widely accepted theory on the formation of secondary eyewall structures. Many previous studies focused on dynamic processes in the inner core of a tropical cyclone that would precede and ultimately lead to the formation of a secondary eyewall. Hurricanes Katrina and Rita in 2005 were frequently

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43

Ezzine, Mouhamed Mounibe. "Etude de dispositifs passifs et actifs de réduction du bruit d’interaction soufflante–redresseur." Electronic Thesis or Diss., Ecully, Ecole centrale de Lyon, 2024. http://www.theses.fr/2024ECDL0022.

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Deux approches de diminution du bruit d'origine aéroacoustique associé à l'OGV des moteurs d'avion ont été examinées dans cette thèse. La première repose sur des solutions passives, utilisant des matériaux comme de la mousse poreuse et du tissu métallique (wire mesh) pour atténuer le bruit. L'efficacité de ces matériaux a été testée dans diverses configurations, montrant une capacité de réduction du bruit jusqu'à 6 dB sous certaines conditions, bien que cette efficacité puisse être affectée par des facteurs comme la vitesse de l'écoulement. La seconde partie de l'étude s'est intéressée aux tec

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44

Kincová, Daniela. "Zavedení a provoz supersonického business jetu." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2015. http://www.nusl.cz/ntk/nusl-232021.

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Tato práce se zabývá problematikou zavedení a provozu nadzvukových business jetů. V dnešní době se v civilní letecké přepravě, po ukončení provozu Concordu, žádná nadzvuková letadla nevyskytují. V dnešní době existuje mnoho projektů a organizací, které se zabývají znovuzavedením nadzvukových letounů do civilního letectví a soustředí se převážně na business jety. Hlavní otázkou je, zda je vůbec vhodné, či rozumné se k tomu typu dopravy znovu vracet. Existuje hodně problémů, které toto komplikují. Tyto letouny způsobují příliš velký hluk, mají obrovskou spotřebu paliva a musí řešit nadměrné emis

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45

"Simulation of turbulent aircraft wake vortex flows and their impact on the signals returned by a coherent Doppler LIDAR system." Université catholique de Louvain, 2008. http://edoc.bib.ucl.ac.be:81/ETD-db/collection/available/BelnUcetd-02182008-162330/.

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46

Poletika, Nicole Marie. ""Wake up! Sign up! Look up!" : organizing and redefining civil defense through the Ground Observer Corps, 1949-1959." Thesis, 2013. http://hdl.handle.net/1805/4081.

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Indiana University-Purdue University Indianapolis (IUPUI)<br>In the early 1950s, President Dwight Eisenhower encouraged citizens to “Wake Up! Sign Up! Look Up!” to the Soviet atomic threat by joining the Ground Observer Corps (GOC). Established by the United States Air Force (USAF), the GOC involved civilian volunteers surveying the skies for Soviet aircraft via watchtowers, alerting the Air Force if they suspected threatening aircraft. This thesis examines the 1950s response to the longstanding problem posed by the invention of any new weapon: how to adapt defensive technology to meet the pot

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47

Pereira, da Silva Carlos Manuel Baptista. "Lamb wave based structural health monitoring of aircraft structures." Thesis, 2010. http://hdl.handle.net/1828/3630.

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Structural Health Monitoring (SHM) through adequate damage detection and prediction of the remaining useful life of structures is a major area of interest in the aerospace community, where the growing maintenance costs can reduce the operational life of flight vehicles. The objective of a SHM system with an advanced diagnostic capability is to gradually replace current schedule-based maintenance tasks, where components are inspected following a pre-established number of cycles using condition-based maintenance, or are maintained prior to attaining an insufficient remaining useful life, based o

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Chang, Ting-Hao, and 張廷豪. "Decay of the Viscous Vortex-Wakes behind a Large Aircraft." Thesis, 1999. http://ndltd.ncl.edu.tw/handle/35509791797719052956.

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碩士<br>國立成功大學<br>航空太空工程學系<br>87<br>The wingtip trailing vortexes generated by a large aircraft are known to be stable and persistent for several miles. Since tip vortexes would cause hazardous problems in airworthiness, the prediction of the descent and decay of the vortex motion is an important factor in determining safe separation between aircrafts during landing and take-off, or flight encounter in air. The objective of this research employs the finite volume method to simulate flow fields including both wing flow and its tip vortexes. A three-dimensional full Navier-Stokes equati

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(8028554), Yiming Wang. "PROPAGATION OF EN-ROUTE AIRCRAFT NOISE." Thesis, 2019.

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The prediction of the noise generated by en-route aircraft is gradually gaining in importance as the number of aircraft increases over the last few decades. While the studies of outdoor sound propagation have been focused on near ground propagation, the case when the sound source is high above the ground has not attracted much attention. At the same time there has been a lack of high-quality aircraft acoustic validation data sets that contain detailed acoustic, meteorology, and source-receiver position data. The DISCOVER-AQ data set, which was collected by Volpe in support of the Federal Aviat

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Ajith, V. "Wave Propagation in Healthy and Defective Composite Structures under Deterministic and Non-Deterministic Framework." Thesis, 2012. http://etd.iisc.ac.in/handle/2005/3253.

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Composite structures provide opportunities for weight reduction, material tailoring and integrating control surfaces with embedded transducers, which are not possible in conventional metallic structures. As a result there is a substantial increase in the use of composite materials in aerospace and other major industries, which has necessitated the need for structural health monitoring(SHM) of aerospace structures. In the context of SHM of aircraft structures, there are many areas, which are still not explored and need deep investigation. Among these, one of the major areas is the development o

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