Дисертації з теми "Hypersonic propulsion and hypersonic aerothermodynamics"
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Fico, Vincenzo. "A high-order method for computational hypersonic aerothermodynamics." Thesis, University of Strathclyde, 2011. http://oleg.lib.strath.ac.uk:80/R/?func=dbin-jump-full&object_id=16946.
Повний текст джерелаFiala, Abderrahmane. "Aerothermodynamics of turbulent spots and wedges at hypersonic speeds." Thesis, Imperial College London, 2005. http://hdl.handle.net/10044/1/12013.
Повний текст джерелаSong, Dong Joo. "Hypersonic nonequilibrium flow over an ablating teflon surface." Diss., Virginia Polytechnic Institute and State University, 1986. http://hdl.handle.net/10919/71192.
Повний текст джерелаPh. D.
Wilson, Althea Grace. "Numerical study of energy utilization in nozzle/plume flow-fields of high-speed air-breathing vehicles." Diss., Rolla, Mo. : Missouri University of Science and Technology, 2008. http://scholarsmine.mst.edu/thesis/pdf/Wilson_09007dcc804d881b.pdf.
Повний текст джерелаVita. The entire thesis text is included in file. Title from title screen of thesis/dissertation PDF file (viewed April 25, 2008) Includes bibliographical references (p. 57).
Bae, Yoon-Yeong. "Performance of an aero-space plane propulsion nozzle /." Full-text version available from OU Domain via ProQuest Digital Dissertations, 1989.
Знайти повний текст джерелаDellaFera, Andrew Brian. "Optimization of Hypersonic Airbreathing Propulsion Systems through Mixed Analysis Methods." Thesis, Virginia Tech, 2019. http://hdl.handle.net/10919/95512.
Повний текст джерелаMaster of Science
Ramjets and scramjets are the key to sustained flight at speeds above five times the speed of sound. These propulsion systems pose a challenging simulation environment due to the wide range of flow seen by the system structure. A scramjet simulation model is formulated using a series of combustion models with the goal of accurately modelling the combustion processes throughout the engine. The combustor model is paired with an isolator model and the engine model is compared against previous studies. A structural analysis model is then paired with the engine simulation, and the combined model is used within an optimizer to find an optimum design.
Halls-Moore, Michael Louis. "Computational modelling of hypersonic propulsion intakes at off-design conditions." Thesis, Imperial College London, 2009. http://hdl.handle.net/10044/1/59000.
Повний текст джерелаZoebelein, Till. "Development of an LU-scheme for the solution of hypersonic non-equilibrium flow." Thesis, Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/12509.
Повний текст джерелаSilton, Sidra Idelle. "Ablation onset in unsteady hypersonic flow about nose-tips with a forward-facing cavity." Access restricted to users with UT Austin EID Full text (PDF) from UMI/Dissertation Abstracts International, 2001. http://wwwlib.umi.com/cr/utexas/fullcit?p3023560.
Повний текст джерелаGupta, Anurag. "The artificially blunted leading edge concept for aerothermodynamic performance enhancement." Diss., Georgia Institute of Technology, 1999. http://hdl.handle.net/1853/12442.
Повний текст джерелаBhutta, Bilal A. "A new parabolized Navier-Stokes scheme for hypersonic reentry flows." Diss., Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/52287.
Повний текст джерелаPh. D.
Henderson, Sean James. "Study of the Issues of Computational Aerothermodynamics Using a Riemann Solver." Wright State University / OhioLINK, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=wright1211933128.
Повний текст джерелаBradford, John Edward. "A technique for rapid prediction of aftbody nozzle performance for hypersonic launch vehicle design." Diss., Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/12896.
Повний текст джерелаContreras, Daimer Mauthsud Leovan Ospina. "Angle of attack impact in the aerothermodynamics of a hypersonic vehicle with surface discontinuity-like a cavity." Instituto Nacional de Pesquisas Espaciais (INPE), 2017. http://urlib.net/sid.inpe.br/mtc-m21b/2017/04.12.00.58.
Повний текст джерелаO estudo descrito nesta dissertação foi realizado com o propósito de investigar o impacto de descontinuidades presentes na superfície de veículos espaciais hipersônicos. Em busca deste propósito, simulações computacionais de um escoamento hipersônico rarefeito não-reativo sobre uma cavidade foram realizadas usando-se o método Direct Simulation Monte Carlo. As simulações forneceram informações detalhadas sobre a natureza da estrutura do escoamento, propriedades primárias e propriedades aerodinâmicas, em função de mudanças na razão comprimento-profundidade (L/H) da cavidade, e mudanças no ângulo de ataque do escoamento incidindo sobre a cavidade. Uma descrição detalhada, das propriedades primárias (velocidade, massa específica, pressão e temperatura) e das quantidades aerodinâmica na superfície (transferência de calor, pressão e atrito), foi obtida por um método numérico que leva em conta adequadamente os efeitos de não-equilíbrio no regime de transição. Os resultados, para cavidades definidas por L/H de 1, 2, 3 e 4, com ângulos de ataque do escoamento de 10, 15 e 20 graus, foram comparados com os de uma placa plana sem/com a presença de cavidade sem/com incidência. A análise mostrou que a topologia do escoamento dentro da cavidade, composta por regiões de recirculação,dependeu da razão L/H bem como do ângulo de ataque do escoamento, para as condições investigadas. Para L/H < 3, observou-se a formação de um único vórtice ocupando inteiramente a cavidade. Para cavidade com L/H =3 e 4, dois vórtices foram formados dentro da cavidade, nas vizinhanças das faces a montante e a jusante da cavidade. A análise também mostrou que, para uma cavidade com L/H = 4 e 10 graus de incidência, a estrutura do escoamento dentro da cavidade correspondeu aquela de uma cavidade fechada , conforme definido para um escoamento no regime do contínuo. Por outro lado, para L/H = 4 e maiores ângulos de incidência, a estrutura do escoamento correspondeu aquela de uma cavidade aberta , para os ângulos de ataque investigados. Outrossim, verificou-se que os valores máximos para os coeficientes de transferência de calor, pressão e coeficiente de atrito ocorreram na superfície a montante do escoamento dentro da cavidade. Verificou-se também que, os valores máximos para o coeficiente de transferência de calor dentro da cavidade aumentaram com o aumento do ângulo de ataque $\alpha$. Todavia, esses valores máximos foram menores do que aqueles observados sobre uma placa plana sem cavidade com incidência. Como resultado, em termos de pressão, a presença da cavidade sobre a superfície do veículo não pode ser ignorada no projeto do veículo.
Dreyer, Emily Rose. "Assessment of Reduced Fidelity Modeling of a Maneuvering Hypersonic Vehicle." The Ohio State University, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=osu1610018486409227.
Повний текст джерелаZhang, Huaibao. "HIGH TEMPERATURE FLOW SOLVER FOR AEROTHERMODYNAMICS PROBLEMS." UKnowledge, 2015. https://uknowledge.uky.edu/me_etds/64.
Повний текст джерелаTorres, Luis Carlos Roldan. "Angle of attack effect in the aerothermodynamics of a hypersonic vehicle with a surface discontinuity of gap type." Instituto Nacional de Pesquisas Espaciais (INPE), 2017. http://urlib.net/sid.inpe.br/mtc-m21b/2017/05.23.23.55.
Повний текст джерелаO desenvolvimento de veículos hipersônicos tem se tornado um tema de interesse nos últimos anos, considerando-se a possibilidade de se chegar com tais veículos a locais até então inacessíveis como os voos orbitais. A construção desses veículos exige materiais especiais e deve apresentar uma forma aerodinâmica eficiente para resistir altas velocidades além de temperaturas elevadas e mudanças de pressão significativas. O estudo descrito nesta dissertação foi realizado com o objetivo de investigar o impacto de descontinuidades presentes na superfície de veículos espaciais hipersônicos. Em busca deste objetivo, simulações computacionais de um escoamento hipersônico rarefeito sobre uma placa plana, foi realizada usando-se o método Direct Simulation Monte Carlo. As simulações forneceram informações sobre a natureza da estrutura do escoamento, propriedades primarias e propriedades aerodinâmicas, devido a variações na razão comprimento-profundidade (L/H), e variações no ângulo de ataque. Uma descrição das propriedades primarias, tais como velocidade, massa específica, pressão e temperatura, e das quantidades aerodinâmica, tais como transferência de calor, pressão e atrito na superfície, foi obtida por um método numérico que leva em conta os efeitos de não-equilíbrio no regime de transição. Os resultados para um filete definido por uma razão L/H de 1, 1/2, 1/3 e 1/4, e com ângulo de ataque do escoamento de 10, 15 e 20 graus, foram comparados com os de uma placa plana sem a presença de um filete. A análise mostrou que a estrutura do escoamento dentro do filete com ângulo de ataque é ligeiramente diferente daquela com zero grau de incidência para cada razão L/H investigada. Verificou-se que os valores máximos para os coeficientes de transferência de calor, pressão e coeficiente de atrito ocorreram na superfície a montante do escoamento dentro do filete. Verificou-se também que, os valores máximos para o coeficiente de transferência de calor dentro do filete aumentaram com o aumento do ângulo de ataque $\alpha$. Como resultado, em termos de pressão, a presença do filete sobre a superfície do veículo não pode ser ignorada no projeto do veículo.
Tirtey, Sandy C. "Characterization of a transitional hypersonic boundary layer in wind tunnel and flight conditions." Doctoral thesis, Universite Libre de Bruxelles, 2009. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/210367.
Повний текст джерелаA wide bibliographic review describing the main parameters affecting transition and their coupling is proposed. The most popular roughness-induced transition predictions correlations are presented, insisting on the lack of physics included in these methods and the difficulties encountered in performing ground hypersonic transition experiments representative of real flight characteristics. This bibliographic review shows the importance of a better understanding of the physical phenomenon and of a wider experimental database, including real flight data, for the development of accurate prediction methods.
Based on the above conclusions, a hypersonic experimental test campaign is realized for the characterization of the flow field structure in the vicinity and in the wake of 3D roughness elements. This fundamental flat plate study is associated with numerical simulations for supporting the interpretation of experimental results and thus a better understanding of transition physics. Finally, a model is proposed in agreement with the wind tunnel observations and the bibliographic survey.
The second principal axis of the present study is the development of a hypersonic in-flight roughness-induced transition experiment in the frame of the European EXPERT program. These flight data, together with various wind tunnel measurements are very important for the development of a wide experimental database supporting the elaboration of future transition prediction methods.
Doctorat en Sciences de l'ingénieur
info:eu-repo/semantics/nonPublished
Rock, Christopher. "Experimental Studies of Injector Array Configurations for Circular Scramjet Combustors." Diss., Virginia Tech, 2010. http://hdl.handle.net/10919/77208.
Повний текст джерелаPh. D.
Perkins, Hugh Douglas. "Development and Demonstration of a Computational Tool for the Analysis of Particle Vitiation Effects in Hypersonic Propulsion Test Facilities." Case Western Reserve University School of Graduate Studies / OhioLINK, 2009. http://rave.ohiolink.edu/etdc/view?acc_num=case1227553721.
Повний текст джерелаLewis, Mark Joel. "The prediction of inlet flow stratification and its influence on the performance of air-breathing hypersonic propulsion systems." Thesis, Massachusetts Institute of Technology, 1988. http://hdl.handle.net/1721.1/14370.
Повний текст джерелаTran, Kathleen. "One Dimensional Analysis Program for Scramjet and Ramjet Flowpaths." Thesis, Virginia Tech, 2010. http://hdl.handle.net/10919/30857.
Повний текст джерелаMaster of Science
Crowell, Andrew R. "Model Reduction of Computational Aerothermodynamics for Multi-Discipline Analysis in High Speed Flows." The Ohio State University, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=osu1366204830.
Повний текст джерелаBonanos, Aristides Michael. "Scramjet Operability Range Studies of an Integrated Aerodynamic-Ramp-Injector/Plasma-Torch Igniter with Hydrogen and Hydrocarbon Fuels." Diss., Virginia Tech, 2005. http://hdl.handle.net/10919/28847.
Повний текст джерелаPh. D.
Bailet, Gilles. "Radiation and ablation studies for in-flight validation." Thesis, Université Paris-Saclay (ComUE), 2019. http://www.theses.fr/2019SACLC008.
Повний текст джерелаUnveiling the mysteries of the solar system to understand the mechanisms of Earth’s formation, to search for signs of life, or to develop settlements on other planets, depends on our abilities to push the limits of engineering and science. One of the key aspects of space exploration is the development of advanced technologies to sustain the entry/reentry phase. During entry or reentry, the spacecraft may be exposed to intense radiative fluxes that cannot be accurately predicted yet, thus imposing high safety margins on the design of thermal protection systems. These uncertainties rise when the heat shield is made of an ablative material as its degradation introduces new chemical species reacting with the flow affecting radiation processes. The goal of this thesis is to study the radiative heat fluxes onto a small size reentry vehicle in the presence of an ablative TPS, using numerical simulations and experiments to develop a flight instrument that will be carried onboard the QARMAN CubeSat.An assessment of the reentry trajectory of the 5-kg QARMAN vehicle was performed using a custom 6-degree of freedom code. An extensive set of Monte Carlo simulations allowed to quantify uncertainties and showed a maximum of ±15% deviation from the nominal trajectory. The spectra without ablation were then computed using a decoupled approach with two codes: Stagline (VKI) and SPECAIR (EM2C, CentraleSupélec). These simulations were performed for the nominal trajectory as well as for the range of uncertainties. They showed a nonlinear behavior of the spectral features deviations from nominal with a drastic increase toward the end of the mission.The effects of ablation were studied with a new measurement technique developed during this thesis. Based on two radiation measurement probes, one cooled and the other with an ablative surface, it allows to quantify the emission and absorption induced by any kind of TPS having gas-surface interactions with the flow, provided that the radiative emission or absorption features of the ablative species do not fully overlap. The method was validated on a graphite TPS sample. It was then applied to determine the radiation expected during the QARMAN mission (Cork P50 TPS). This study also allowed to select an emission spectrometer (350-800 nm range for a 68-g mass).A standard radiation instrument was tested and the limits of this device shown. On those lessons learned, two new technologies were developed and an emission spectrometer payload (INES) was built and integrated into the QARMAN reentry CubeSat. A dedicated spectral and thermal calibration was also developed to maximize the quality of the scientific return by tackling the non-standard internal temperature variations of QARMAN’s payload bay.Relying on two inventions made during this study, the apparatus is at the time of writing, the only non-intrusive payload capable of making radiative measurements without limitations due to ablation dust contamination. The instrument can also provide measurements of recession, sublimation and swelling of the TPS with a precision of at least 0.2 mm. Operation of the apparatus was demonstrated for a wide variety of test conditions, including different enthalpy profiles, gas mixtures and TPS materials
Benyo, Theresa L. "Analytical and Computational Investigations of a Magnetohydrodynamic (MHD) Energy-Bypass System for Supersonic Turbojet Engines to Enable Hypersonic Flight." Kent State University / OhioLINK, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=kent1369153719.
Повний текст джерелаMorham, Brett G. "Numerical Examination of Flow Field Characteristics and Fabri Choking of 2D Supersonic Ejectors." DigitalCommons@CalPoly, 2010. https://digitalcommons.calpoly.edu/theses/340.
Повний текст джерелаFerrier, Loïc. "Analyse aérothermodynamique de l'entrée atmosphérique d'un géocroiseur à occurence séculaire." Thesis, Toulouse, ISAE, 2012. http://www.theses.fr/2012ESAE0017/document.
Повний текст джерелаNear Earth Objects (NEOs) impact Earth everyday. When the objet reaches a critical size (>50m), ground consequences might be dramatic. Moreover, NEOs have a secular occurrence, i.e. at a human scale. A NEO entry object involves various phenomena, poorly or not known: flow AeroThermoDynamics (ATD), radiation, ablation, fragmentation. The variety ofstudied entry conditions implies also an extensive parametric study. My thesis is that the entry and the phenomena that take place in this phase has a crucial role in the prediction of impact consequences. That why I have quantified these phenomena in order to assess their consequences on the ground impact: number and sizgg of the fragments, ground print, velocity, mass and kinetic energy. ATD simulations showed the aftershock flow was in thermochemical equilibrium, and highly radiates. In order to correctly estimate the radiative flux for the entry conditions of a NEO, an analytical law has been developed. During its entry, a NEO loses mass and change its shape because of ablation.To estimate the consequence on the trajectory of the NEO, two models of this phenomenon have been elaborated. Fragmentation has been modelled, from the origin of breakup to the mechanism offragment generation and flight dynamics of these fragments. This study showed the importance of these phenomena on ground consequences prediction, especially on the number of fragments impacting, their kinetic energies, and their positions on ground. Eventually, trajectory simulations (1 D&3 D), ta ken into account these phenomena, have been conducted. They highlighted the importance ofentry speed and slope on ground consequences.These simulations also demonstrated the protective role of the atmosphere on ground consequences, especially because of the fragmentation
Retaureau, Ghislain J. "On recessed cavity flame-holders in supersonic cross-flows." Diss., Georgia Institute of Technology, 2012. http://hdl.handle.net/1853/43703.
Повний текст джерелаMartos, João Felipe de Araújo. "Investigação experimental do veículo hipersônico aeroespacial 14-XB." reponame:Repositório Institucional da UFABC, 2014.
Знайти повний текст джерелаDissertação (mestrado) - Universidade Federal do ABC, Programa de Pós-Graduação em Engenharia Mecânica, 2014.
O veículo hipersônico aeroespacial brasileiro 14-X B (VHA 14-X B) é um demonstrador tecnológico do sistema de propulsão hipersônica aspirada com base em combustão supersônica (scramjet) projetado para voar na atmosfera da Terra a 30 quilômetros de altitude e número de Mach 7. O VHA 14-X B encontra-se em desenvolvimento no Laboratório de Aerotermodinâmica e Hipersônica Professor Henry T. Nagamatsu do Instituto de Estudos Avançados (IEAv). Uma das metodologias mais importantes na análise e desenvolvimento de um veículo aeroespacial hipersônico são os túneis de vento hipersônicos pulsados, os quais são instalações experimentais em terra capazes de simular as condições de voo, fornecendo dados experimentais para o projeto dos veículos aeroespaciais hipersônicos. Neste trabalho, foi utilizado o túnel de vento hipersônico pulsado T3 que possui 61 cm de diâmetro no bocal de saída e é operado com base na técnica de onda de choque refletida. O T3 foi financiado pela Fundação de Amparo a Pesquisa de São Paulo (FAPESP) e foi projetado para Pesquisa e Desenvolvimento na área de combustão supersônica. Trata-se de um tubo de choque equipado com um bocal convergente-divergente utilizado para produzir elevado número Mach e escoamentos de alta entalpia na seção de teste próximos aos encontrados durante o voo de um veículo aeroespacial na atmosfera da Terra a hipervelocidade. O modelo de 1 metro de comprimento em aço inoxidável do 14-X B foi instrumentado, com vinte e oito transdutores de pressão piezelétricos PCB nas superfícies de compressão, câmara de combustão e de expansão. Utilizando o túnel T3 no modo de operação de equilíbrio de interface para atingir escoamento livre com número de Mach entre 7 e 8 foi realizada a investigação experimental. Medidas da pressão estática no intradorso do modelo 14-X B, bem como fotografias schlieren, feitas a partir do bordo de ataque do modelo forneceram dados experimentais, que foram comparados com as análises teórica-analítica e simulações computacionais de dinâmica de fluidos, ambos utilizadas no projeto do modelo do VHA 14-X B.
The Brazilian VHA 14-X B is a technological demonstrator of a hypersonic airbreathing propulsion system based on the supersonic combustion (scramjet) intended to fly into the Earth¿s atmosphere at 30 km altitude and Mach number 7. The 14-X B was designed o the Prof. Henry T. Nagamatsu Laboratory of Aerothermodynamics and Hypersonics of the Institute for Advanced Studies (IEAv). Hypersonic wind tunnels are one of the most important ground-based experimental facilities intended to simulate the flight conditions providing experimental data to design hypersonic aerospace vehicles and engines. The IEAv 0.60-m nozzle exit diameter Hypersonic Reflected Shock Tunnel named T3 and funded by São Paulo Research Foundation (FAPESP), was designed as a research & development facility for basic investigations in supersonic combustion. The T3 Hypersonic Shock Tunnel is a shock tube equipped with a convergent-divergent nozzle to produce high Mach number and high enthalpy flows in the test section close to those encountered during the flight of a aerospace vehicle into the Earth's atmosphere at hypersonic flight speeds. A 1-m long stainless steel VHA 14-X B model was instrumented with twenty-eight piezoelectric pressure transducers along its compression surface, combustion chamber and nozzle. It was experimentally investigated on the equilibrium interface operational mode of the T3 Hypersonic Shock Tunnel, yielding a freestream Mach number from 7 to 8. Static pressure measurements at the lower surface of the VHA 14-X B as well as high speed schlieren photographs taken from the 5.5° leading edge and the 14.5° deflection compression ramp provide experimental data that was compared to the analytic theoretical analysis and computational fluid dynamics simulation, both applied to the design of the VHA 14-X B.
Poulain, François. "Commande d'un véhicule hypersonique à propulsion aérobie : modélisation et synthèse." Phd thesis, Ecole Nationale Supérieure des Mines de Paris, 2012. http://pastel.archives-ouvertes.fr/pastel-00744985.
Повний текст джерелаYentsch, Robert J. "Three-Dimensional Shock-Boundary Layer Interactions in Simulations of HIFiRE-1 and HIFiRE-2." The Ohio State University, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=osu1384195671.
Повний текст джерелаHima, Bindu V. "Experimental Investigations Of Aerothermodynamics Of A Scramjet Engine Configuration." Thesis, 2009. http://hdl.handle.net/2005/1120.
Повний текст джерелаHarrland, Alan. "Hypersonic inlet for a laser powered propulsion system." Thesis, 2012. http://hdl.handle.net/2440/79072.
Повний текст джерелаThesis (M.Phil.) -- University of Adelaide, School of Mathematical Sciences, 2012
Nagashetty, K. "Experimental Investigations on Hypersonic Waverider." Thesis, 2014. http://hdl.handle.net/2005/3195.
Повний текст джерелаSaravanan, S. "Experimental Investigation Of The Effect Of Nose Cavity On The Aerothermodynamics Of The Missile Shaped Bodies Flying At Hypersonic Mach Numbers." Thesis, 2007. http://hdl.handle.net/2005/694.
Повний текст джерела"Parametric Analysis of a Hypersonic Inlet using Computational Fluid Dynamics." Master's thesis, 2013. http://hdl.handle.net/2286/R.I.20879.
Повний текст джерелаDissertation/Thesis
M.S. Aerospace Engineering 2013
Silton, Sidra Idelle 1973. "Ablation onset in unsteady hypersonic flow about nose-tips with a forward-facing cavity." 2001. http://hdl.handle.net/2152/10834.
Повний текст джерела(8032571), Varun Viswanathan. "Hypersonic Stationary Crossflow Waves: Receptivity to Roughness." Thesis, 2019.
Знайти повний текст джерела(6624017), Joshua B. Edelman. "Nonlinear Growth and Breakdown of the Hypersonic Crossflow Instability." Thesis, 2019.
Знайти повний текст джерела(6623855), Mark Wason. "CALIBRATION OF HIGH-FREQUENCY PRESSURE SENSORS USING LOW-PRESSURE SHOCK WAVES." Thesis, 2019.
Знайти повний текст джерела(7399604), Phillip Portoni. "Using Suction for Laminar Flow Control in Hypersonic Quiet Wind Tunnels: A Feasibility Study." Thesis, 2019.
Знайти повний текст джерела"Modeling, Analysis, and Control of a Hypersonic Vehicle With Significant Aero-Thermo-Elastic-Propulsion Interactions, and Propulsive Uncertainty." Master's thesis, 2010. http://hdl.handle.net/2286/R.I.8592.
Повний текст джерелаDissertation/Thesis
M.S. Electrical Engineering 2010
Chan, Jonathan. "Numerically Simulated Comparative Performance of a Scramjet and Shcramjet at Mach 11." Thesis, 2010. http://hdl.handle.net/1807/25446.
Повний текст джерела(8793053), Gregory R. McKiernan. "Instability and Transition on a Sliced Cone with a Finite-Span Compression Ramp at Mach 6." Thesis, 2020.
Знайти повний текст джерела(9189470), Abhinand Ayyaswamy. "Computational Modeling of Hypersonic Turbulent Boundary Layers By Using Machine Learning." Thesis, 2020.
Знайти повний текст джерела(8292123), Julien Keith Louis Brillon. "Modeling Thermochemical Nonequilibrium Processes and Flow Field Simulations of Spark-Induced Plasma." Thesis, 2020.
Знайти повний текст джерела"Modeling, Analysis, and Control of a Hypersonic Vehicle with Significant Aero-Thermo-Elastic-Propulsion Interactions: Elastic, Thermal and Mass Uncertainty." Master's thesis, 2011. http://hdl.handle.net/2286/R.I.8873.
Повний текст джерелаDissertation/Thesis
M.S. Electrical Engineering 2011
(8960978), Lalit Rajendran. "DEVELOPMENT OF IMAGE-BASED DENSITY DIAGNOSTICS WITH BACKGROUND-ORIENTED SCHLIEREN AND APPLICATION TO PLASMA INDUCED FLOW." Thesis, 2021.
Знайти повний текст джерелаThere is growing interest in the use of nanosecond surface dielectric barrier discharge (ns-SDBD) actuators for high-speed (supersonic/hypersonic) flow control. A plasma discharge is created using a nanosecond-duration pulse of several kilovolts, and leads to a rapid heat release and a complex three-dimensional flow field. Past work has been limited to qualitative visualizations such as schlieren imaging, and detailed measurements of the induced flow are required to develop a mechanistic model of the actuator performance.
Background-Oriented Schlieren (BOS) is a quantitative variant of schlieren imaging and measures density gradients in a flow field by tracking the apparent distortion of a target dot pattern. The distortion is estimated by cross-correlation, and the density gradients can be integrated spatially to obtain the density field. Owing to the simple setup and ease of use, BOS has been applied widely, and is becoming the preferred density measurement technique. However, there are several unaddressed limitations with potential for improvement, especially for application to complex flow fields such as those induced by plasma actuators.
This thesis presents a series of developments aimed at improving the various aspects of the BOS measurement chain to provide an overall improvement in the accuracy, precision, spatial resolution and dynamic range. A brief summary of the contributions are:
1) a synthetic image generation methodology to perform error and uncertainty analysis for PIV/BOS experiments,
2) an uncertainty quantification methodology to report local, instantaneous, a-posteriori uncertainty bounds on the density field, by propagating displacement uncertainties through the measurement chain,
3) an improved displacement uncertainty estimation method using a meta-uncertainty framework whereby uncertainties estimated by different methods are combined based on the sensitivities to image perturbations,
4) the development of a Weighted Least Squares-based density integration methodology to reduce the sensitivity of the density estimation procedure to measurement noise.
5) a tracking-based processing algorithm to improve the accuracy, precision and spatial resolution of the measurements,
6) a theoretical model of the measurement process to demonstrate the effect of density gradients on the position uncertainty, and an uncertainty quantification methodology for tracking-based BOS,
Then the improvements to BOS are applied to perform a detailed characterization of the flow induced by a filamentary surface plasma discharge to develop a reduced-order model for the length and time scales of the induced flow. The measurements show that the induced flow consists of a hot gas kernel filled with vorticity in a vortex ring that expands and cools over time. A reduced-order model is developed to describe the induced flow and applying the model to the experimental data reveals that the vortex ring's properties govern the time scale associated with the kernel dynamics. The model predictions for the actuator-induced flow length and time scales can guide the choice of filament spacing and pulse frequencies for practical multi-pulse ns-SDBD configurations.
Perez, Jaime Enrique. "EVALUATION OF GEOMETRIC SCALE EFFECTS FOR SCRAMJET ISOLATORS." 2010. http://trace.tennessee.edu/utk_gradthes/739.
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