Tesis sobre el tema "Aircraft wake"
Crea una cita precisa en los estilos APA, MLA, Chicago, Harvard y otros
Consulte los 50 mejores tesis para su investigación sobre el tema "Aircraft wake".
Junto a cada fuente en la lista de referencias hay un botón "Agregar a la bibliografía". Pulsa este botón, y generaremos automáticamente la referencia bibliográfica para la obra elegida en el estilo de cita que necesites: APA, MLA, Harvard, Vancouver, Chicago, etc.
También puede descargar el texto completo de la publicación académica en formato pdf y leer en línea su resumen siempre que esté disponible en los metadatos.
Explore tesis sobre una amplia variedad de disciplinas y organice su bibliografía correctamente.
Stephan, Anton. "Wake vortices of landing aircraft". Diss., Ludwig-Maximilians-Universität München, 2014. http://nbn-resolving.de/urn:nbn:de:bvb:19-167566.
Texto completoBertényi, Tamás. "Merger of aircraft wake vortices". Thesis, University of Cambridge, 2002. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.620288.
Texto completoRodenhiser, Rebecca J. "An Ultrasonic Method for Aircraft Wake Vortex Detection". Digital WPI, 2005. https://digitalcommons.wpi.edu/etd-theses/1004.
Texto completoRodenhiser, 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/.
Texto completoMarles, 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.
Texto completoAndronache, Constantin. "A study of aerosol interactions in aircraft wake and background atmosphere". Diss., Georgia Institute of Technology, 1996. http://hdl.handle.net/1853/26008.
Texto completoStephan, Anton [Verfasser] y 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.
Texto completoRoa, 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.
Texto completoPHD
Craig, Margaret Elizabeth. "Trailing-Edge Blowing of Model Fan Blades for Wake Management". Thesis, Virginia Tech, 2005. http://hdl.handle.net/10919/30886.
Texto completoMaster of Science
Schroeder, Nataliya. "Analysis of Potential Wake Turbulence Encounters in Current and NextGen Flight Operations". Thesis, Virginia Tech, 2011. http://hdl.handle.net/10919/40924.
Texto completoMaster of Science
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.
Texto completoCataloged from PDF version of thesis.
Includes bibliographical references (p. 105-107).
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 drag sphere with allocation to continue to various shapes and sizes. A parametric study is conducted which highlights the effect of changing the parameters of towline material, length, and load factor. Three maneuvers are conducted including a turn and acceleration. The results show that longer cable lengths, those of 500 m or greater, exhibit little response to the addition of a trailing wake. However, shorter cables are affected, especially during the turn and climb maneuvers. A 50 m cable experiences an extra 8m deflection when compared to a wake-less example. During the climb maneuver, it is shown that an endbody may pass ahead of the towing aircraft, as well as above it. The effect of changing cable material is shown to be minimal, with small differences expected due to the difference in cable mass.
by Jacob Thomas Hall.
S.M.
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.
Texto completoPh. D.
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.
Texto completoTrupka, 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.
Texto completoDepartment of Mechanical and Nuclear Engineering
Mohammad H. Hosni
Byron W. Jones
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 remove these harmful contaminates as quickly as possible to minimize spread in cabin air. Disruptions to the design airflow pattern can hinder the effectiveness of contamination removal efforts. A common form of this airflow disruption is longitudinal air movement through cabin aisles. To examine the effect of contaminate transport down aircraft aisles by a moving body, a motorized beverage cart is past by a contamination source as it traverses the length of the cabin aisle. An experimental study is performed in a mockup Boeing 767 cabin section consisting of eleven rows with seven seats per row. Carbon Dioxide (CO2) tracer gas is injected at a constant flow rate at a location of interest until concentrations in the cabin reach steady state. Ventilation equipment and flow rates representative of an actual aircraft are used for all experiments. Seats in the mockup are occupied by thermal manikins to simulate passenger heat load. A motorized beverage cart traverses the length of the cabin aisle passing by the injection location. The concentrations of tracer gas displaced by the cart are measured at locations throughout the cabin. Comparing these measurements to baseline readings taken with no cart movement, a map of the degree to which contaminant transport is affected by the beverage cart is calculated. The cabin mockup is supplied by 100% outdoor air through actual Boeing supply ductwork and linear diffusers along the cabin length above the aisles. The CO2 level is measured in the inlet air, measurement locations in the cabin, and exhaust air using nondispersive infrared (NDIR) sensors. Measured results are reported for all (54) seat locations downstream of the cart traverse/injection location for an injection location near the rear of the cabin. Analogous measurements are also conducted examining the effect of variations in cart speed and modified injection location. It was found the beverage cart movement had an effect of up to a 35% increase in tracer gas concentration relative to the local steady state concentration for several seat locations adjacent to the aisle. This increased concentration continued for only a few minutes in all cases, but was generally less than the steady state exposure one row closer to the injection location. Moving in the lateral direction away from the aisle, the variance in tracer gas concentration due to the cart movement diminished quickly. The significance of increased concentration for such short periods of time in comparison to the length of actual commercial flights may require further biological analysis. The data showed general tracer gas concentration increases due to cart movement in a small section of the cabin mockup which could warrant further analysis, but increases were generally insignificant when considering entire flight contamination exposure levels.
Mauermann, Tobias [Verfasser] y 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.
Texto completoFrink, 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.
Texto completoA 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 model lengths downstream of the model. The effect of adding a fence to the leading edge extension (LEX) was studied. Power spectra from the hot-wire were recorded for the survey station directly aft of the model. Results show that: peak turbulent fluctuation at this station occurred at 25 deg angle of attack; lateral turbulent fluctuation greatly diminished at the far downstream station; and the addition of the LEX fence shifted energy content of turbulence toward higher frequencies.
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.
Texto completoThesis 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 Measurements, Wind Tunnel Studies. Includes bibliographical references (p. 24-25). Also available in print.
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.
Texto completoMaster of Science
Mirmohammadsadeghi, Navid. "Improvements to Airport Systems Capacity and Efficiency Using Computer Models and Tools". Thesis, Virginia Tech, 2017. http://hdl.handle.net/10919/84301.
Texto completoMaster of Science
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.
Texto completoContrails are ice clouds that form in the wake of aircraft. Their study, including their meteorological impact, is made difficult by the need to understand numerous spatial and temporal scales, from engine output to induced cirrus clouds whose extension can reach several hundred square kilometers. This thesis focuses on the influence of wake vortices, also known as tip vortices, on the distribution of the engine plume and the condensation of water vapour into ice, from their rolling up to their destabilization, passing through a two-dimensional phase where the dynamics of these longitudinal vortices are dominant. The thermal stratification of the atmosphere plays a major role in their evolution. In particular, the natural movement of vortices is downwards, but a secondary wake can form in their vicinity and then rise back up to flight altitude. The dynamic wake is then separated into two distinct components. Engine plumes can find themselves caught in one or the other, depending on their initial position. In supersaturated zones, this has a strong influence on condensation within the plume, given temperature variations with altitude, and therefore on its optical impact
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.
Texto completoDen här avhandlingen undersöker det turbulenta flödet runt övergången mellan flygplanskropp och vinge på en NASA Common Research Model för att vidare utforska den komplexa, tredimensionella strukturen av flödet och bidra till NASA’s officiella databas för jämförelser med simulerade flöden. Kompressibla flöden nära tvåväggsgränsskikt uppkommer inte bara vid övergången mellan flygplanskropp och vinge utan även vid varje kontrollyta på ett flygplan. Ökad kunskap om flödets beteende vid sådana områden kan därför bidra till en bättre uppskattning av prestanda och effektivitet av kontrollytorna och flygplanet i sin helhet, vilket kan bidra till minskad miljöpåverkan från kommersiell flygtrafik. Flygplansmodellen är modifierad genom montering av en vingklaff på den inre delen av vingen, detta för att undersöka hur olika vinklar på klaffarnas nedböjning påverkar flödets struktur och hastighetsfält. Framtida klaffdesigner och inställningar för ökad prestanda diskuteras även utifrån denna påverkan. Mätningarna i vindtunneln gjordes med en Cobra Probe, ett dynamisk tryckmätningsinstrument, speciellt designad för turbulenta och instabila flöden. Reynoldsnumren som generades av den subsoniska, indrags-vindtunneln var ungefär en miljon baserad på vingrotens längd, vilket motsvarar knappt en tiondel av normala flygförhållanden för samma flygplansmodell.
Jugier, Rémi. "Stabilité bidimensionnelle de modèles de sillage d’aéronefs". Thesis, Toulouse, ISAE, 2016. http://www.theses.fr/2016ESAE0021/document.
Texto completoAircraft wake vortex control allows for reducing of their dangerousness and consequently improve airport take-off / landing requencies. Contrails and artificial cirrus clouds formation could also be influenced through this control of wake vortices and allow for reducing of terrestrial radiative forcing generated by aviation. Brion (2014) have shown by a modal stability analysis that the Lamb-Chaplygin dipole, often used as a far-field model for aircraft wake vortices, is unstable to two-dimensional perturbations at Iow Reynolds numbers. We first extend this twodimensional modal stability analysis to more realistic dipole models, for a Wide range of aspect ratios, and obtain, for Iow Reynolds numbers, instabilities of the same nature (displacement modes) as for the Lamb-Chaplygin dipole. However, we show that the growth of those modes depends greatly on the dipole aspect ratio, and that this growth is greatly diminished hen the dipole diffusion is taken into account. We then study two-dimensional transient growth for far-field models (dipoles) and near-field models (vorticity sheets), in homogeneous and stratified atmospheres. ln all cases, optimal perturbations are vorticity spirals oriented against shear and located at the periphery of the vortices, which eventually lead to development of the instabilities described in the modal analysis through a contamination mechanism of the vortex cores, initially identified by Antkowiak & Brancher (2004) for an isolated vortex
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.
Texto completoShen, 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.
Texto completoYeung, 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.
Texto completoMaterano, 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.
Texto completoMenday, Roger. "The forced vibration of a partially delaminated beam". Thesis, Loughborough University, 1999. https://dspace.lboro.ac.uk/2134/27082.
Texto completoKural, Aleksander. "Ultrasonic lamb wave energy transmission system for aircraft structural health monitoring applications". Thesis, Cardiff University, 2013. http://orca.cf.ac.uk/58395/.
Texto completoLambert, Luke. "Efficient probabilistic structural response prediction for aircraft turbulence and offshore wave loading". Thesis, University of Liverpool, 2015. http://livrepository.liverpool.ac.uk/2010819/.
Texto completoHuang, 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.
Texto completoDeLaurentis, 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.
Texto completoRamasamy, 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.
Texto completoLock, 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.
Texto completoThesis advisor(s): David C. Jenn, Jeffrey B. Knorr. Includes bibliographical references (p. 85-87). Also available online.
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.
Texto completoMaster of Science
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/.
Texto completoBramberger, Martina [Verfasser] y 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.
Texto completoWaddington, Michael Jon. "Development of an Interactive Wave Drag Capability for the OpenVSP Parametric Geometry Tool". DigitalCommons@CalPoly, 2015. https://digitalcommons.calpoly.edu/theses/1435.
Texto completoBorgoltz, Aurelien. "Modifications of Coherent Structures in Fan Blade Wakes for Broadband Noise Reduction". Diss., Virginia Tech, 2007. http://hdl.handle.net/10919/29619.
Texto completoPh. D.
Pundarika, G. "Experimental And Theoretical Studies On Jet Acoustics". Thesis, Indian Institute of Science, 2001. https://etd.iisc.ac.in/handle/2005/250.
Texto completoPundarika, G. "Experimental And Theoretical Studies On Jet Acoustics". Thesis, Indian Institute of Science, 2001. http://hdl.handle.net/2005/250.
Texto completoPoh, 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.
Texto completoJudt, Falko. "Convectively-Generated Potential Vorticity in Rainbands and Secondary Eyewall Formation in Hurricanes". Scholarly Repository, 2009. http://scholarlyrepository.miami.edu/oa_theses/214.
Texto completoKincová, 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.
Texto completo"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/.
Texto completoPoletika, 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.
Texto completoIn 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 potential threat. In the case of the early Cold War period, the GOC was the USAF’s best, albeit faulty, defense option against a weapon that did not discriminate between soldiers and citizens and rendered traditional ground troops useless. After the Korean War, Air Force officials promoted the GOC for its espousal of volunteerism and individualism. Encouraged to take ownership of the program, observers appropriated the GOC for their personal and community needs, comprised of social gatherings and policing activities, thus greatly expanding the USAF’s original objectives.
Pereira, da Silva Carlos Manuel Baptista. "Lamb wave based structural health monitoring of aircraft structures". Thesis, 2010. http://hdl.handle.net/1828/3630.
Texto completoGraduate
Chang, Ting-Hao y 張廷豪. "Decay of the Viscous Vortex-Wakes behind a Large Aircraft". Thesis, 1999. http://ndltd.ncl.edu.tw/handle/35509791797719052956.
Texto completo國立成功大學
航空太空工程學系
87
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 equations solver, CFD-2000 flow analysis system, is used to calculate the steady, low-speed Newtonian viscous flow over a rectangular wing with NACA 0012 sections. The vortex wake flows are simulated by turbulent and laminar flow, respectively. In this thesis, the vortex center and vortex core radius are defined by velocity and by vorticity distribution on every cross flow section in the vortex wake. The descent of the vortex center and vortex span, the growth of the vortex radii and the decay of the vortex strength of the vortex are also discussed. The results show that the descent of the vortex center and vortex span in the turbulent case are slower than those in the laminar case. Besides, from the results of more intensive diffusion of the turbulent vortex wakes near the trailing edge of the wing, the vortex strength decays faster in this flow region, but it reaches the same strength as laminar case far downstream of the wake.
(8028554), Yiming Wang. "PROPAGATION OF EN-ROUTE AIRCRAFT NOISE". Thesis, 2019.
Buscar texto completoTo provide a more accurate prediction of en-route aircraft noise, we derived the analytic asymptotic solution of the sound field above a non-locally reacting ground due to a moving point source and a line source using the methods of the steepest descent and a Lorentz transform. The model predicts a much more accurate result for sound field above "soft" grounds, such as a snow-covered ground and sand-covered ground. At the same time, we derived a fast numerical algorithm based on Levin’s collocation for the prediction of the sound field in the presence of a temperature gradient, which can be applied to a wide range of acoustic problems involving integration. The achievements recorded in this thesis can be used to predict the sound field generated by aircraft, trains, and vehicles with a subsonic moving speed. In addition,
the model can be used for detection and design of moving sound source.
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.
Texto completoAjith, V. "Wave Propagation in Healthy and Defective Composite Structures under Deterministic and Non-Deterministic Framework". Thesis, 2012. http://hdl.handle.net/2005/3253.
Texto completo