Thèses sur le sujet « Supersonic / hypersonic »
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Higgins, Andrew J. « Investigation of detonation initiation by supersonic blunt bodies / ». Thesis, Connect to this title online ; UW restricted, 1996. http://hdl.handle.net/1773/10000.
Texte intégralDenman, Paul Ashley. « Experimental study of hypersonic boundary layers and base flows ». Thesis, Imperial College London, 1996. http://hdl.handle.net/10044/1/45466.
Texte intégralHunt, David Leslie. « An investigation of supersonic buffet using a Large Eddy Simulation ». Thesis, Queen's University Belfast, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.318735.
Texte intégralHusmeier, Frank. « Numerical Investigations of Transition in Hypersonic Flows over Circular Cones ». Diss., The University of Arizona, 2008. http://hdl.handle.net/10150/196123.
Texte intégralDel, Rio Francesco. « Distortion mechanism in supersonic combustion ramjet engines ». Master's thesis, Alma Mater Studiorum - Università di Bologna, 2018.
Trouver le texte intégralFuller, Eric James. « Experimental and computational investigation of helium injection into air at supersonic and hypersonic speeds ». Diss., Virginia Tech, 1992. http://hdl.handle.net/10919/39977.
Texte intégralPh. D.
Lee, Jaewoo. « Efficient inverse methods for supersonic and hypersonic body design, with low wave drag analysis ». Diss., Virginia Tech, 1991. http://hdl.handle.net/10919/37406.
Texte intégralPh. D.
Grossman, Peter Michael. « Experimental Investigation of a Flush-Walled, Diamond-Shaped Fuel Injector for High Mach Number Scramjets ». Thesis, Virginia Tech, 2007. http://hdl.handle.net/10919/30974.
Texte intégral
The results of the investigation can be summarized as follows. For the baseline case, the aligned diamond injector penetrated 44% higher into the crossflow than did the round injector. The addition of yaw angle increased the crossflow penetration to 53% higher than the round injector. The aligned diamond injector produced a 34% wider jet than the round injector, while the addition of yaw angle somewhat reduced this widening effect to 26% wider than the round injector. The aligned and yawed diamond injectors exhibited 10% and 15% lower mixing efficiency than the round injector, respectively. The total pressure loss parameter of the aligned diamond was 22% lower than the round injector, while the addition of yaw angle improved the total pressure loss parameter to 34% lower than the round injector. For the lower mass flow (and momentum flux ratio) case, the diamond injector demonstrated 52% higher penetration and a 39% wider plume than the round injector. The mixing efficiency was nearly identical between the two injectors with just a 4% lower mixing efficiency for the diamond injector. The total pressure loss parameter of the diamond injector was 32% lower than round injector. These results confirm the conclusions of earlier, lower free stream Mach number and higher molecular weight injectant, studies that a slender diamond injector provides significant benefits for crossflow penetration and lower total pressure losses.
Master of Science
Schreyer, Anne-Marie [Verfasser]. « Experimental investigations of supersonic and hypersonic shock wave/turbulent boundary layer interactions / Anne-Marie Schreyer ». München : Verlag Dr. Hut, 2013. http://d-nb.info/1045126853/34.
Texte intégralRock, Christopher. « Experimental Studies of Injector Array Configurations for Circular Scramjet Combustors ». Diss., Virginia Tech, 2010. http://hdl.handle.net/10919/77208.
Texte intégralPh. D.
Smith, Theodore Brooke. « Development and Ground Testing of Direct Measuring Skin Friction Gages for High Enthalpy Supersonic Flight Tests ». Diss., Virginia Tech, 2001. http://hdl.handle.net/10919/29351.
Texte intégralPh. D.
Witt, Michael A. « Investigation in the feasibility of using solid fuel ramjets for high supersonic/low hypersonic tactical missiles ». Thesis, Monterey, California. Naval Postgraduate School, 1989. http://hdl.handle.net/10945/26015.
Texte intégralAxdahl, Erik Lee. « A study of premixed, shock-induced combustion with application to hypervelocity flight ». Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/50290.
Texte intégralMalo-Molina, Faure Joel. « Numerical study of innovative scramjet inlets coupled to combustors using hydrocarbon-air mixture ». Diss., Georgia Institute of Technology, 2010. http://hdl.handle.net/1853/33906.
Texte intégralLaible, Andreas Christian. « Numerical Investigation of Boundary-Layer Transition for Cones at Mach 3.5 and 6.0 ». Diss., The University of Arizona, 2011. http://hdl.handle.net/10150/205419.
Texte intégralRetaureau, Ghislain J. « On recessed cavity flame-holders in supersonic cross-flows ». Diss., Georgia Institute of Technology, 2012. http://hdl.handle.net/1853/43703.
Texte intégralBenyo, 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.
Texte intégralGriffiths, Alan David, et alan griffiths@anu edu au. « Development and demonstration of a diode laser sensor for a scramjet combustor ». The Australian National University. Faculty of Science, 2005. http://thesis.anu.edu.au./public/adt-ANU20051114.132736.
Texte intégralBonanos, 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.
Texte intégralPh. D.
Morham, Brett G. « Numerical Examination of Flow Field Characteristics and Fabri Choking of 2D Supersonic Ejectors ». DigitalCommons@CalPoly, 2010. https://digitalcommons.calpoly.edu/theses/340.
Texte intégralBenyo, Theresa Louise. « Analytical and computational investigations of a magnetohydrodynamics (MHD) energy-bypass system for supersonic gas turbine engines to enable hypersonic flight ». Thesis, Kent State University, 2014. http://pqdtopen.proquest.com/#viewpdf?dispub=3618922.
Texte intégralHistorically, the National Aeronautics and Space Administration (NASA) has used rocket-powered vehicles as launch vehicles for access to space. A familiar example is the Space Shuttle launch system. These vehicles carry both fuel and oxidizer onboard. If an external oxidizer (such as the Earth's atmosphere) is utilized, the need to carry an onboard oxidizer is eliminated, and future launch vehicles could carry a larger payload into orbit at a fraction of the total fuel expenditure. For this reason, NASA is currently researching the use of air-breathing engines to power the first stage of two-stage-to-orbit hypersonic launch systems. Removing the need to carry an onboard oxidizer leads also to reductions in total vehicle weight at liftoff. This in turn reduces the total mass of propellant required, and thus decreases the cost of carrying a specific payload into orbit or beyond. However, achieving hypersonic flight with air-breathing jet engines has several technical challenges. These challenges, such as the mode transition from supersonic to hypersonic engine operation, are under study in NASA's Fundamental Aeronautics Program.
One propulsion concept that is being explored is a magnetohydrodynamic (MHD) energy- bypass generator coupled with an off-the-shelf turbojet/turbofan. It is anticipated that this engine will be capable of operation from takeoff to Mach 7 in a single flowpath without mode transition. The MHD energy bypass consists of an MHD generator placed directly upstream of the engine, and converts a portion of the enthalpy of the inlet flow through the engine into electrical current. This reduction in flow enthalpy corresponds to a reduced Mach number at the turbojet inlet so that the engine stays within its design constraints. Furthermore, the generated electrical current may then be used to power aircraft systems or an MHD accelerator positioned downstream of the turbojet. The MHD accelerator operates in reverse of the MHD generator, re-accelerating the exhaust flow from the engine by converting electrical current back into flow enthalpy to increase thrust. Though there has been considerable research into the use of MHD generators to produce electricity for industrial power plants, interest in the technology for flight-weight aerospace applications has developed only recently.
In this research, electromagnetic fields coupled with weakly ionzed gases to slow hypersonic airflow were investigated within the confines of an MHD energy-bypass system with the goal of showing that it is possible for an air-breathing engine to transition from takeoff to Mach 7 without carrying a rocket propulsion system along with it. The MHD energy-bypass system was modeled for use on a supersonic turbojet engine. The model included all components envisioned for an MHD energy-bypass system; two preionizers, an MHD generator, and an MHD accelerator. A thermodynamic cycle analysis of the hypothesized MHD energy-bypass system on an existing supersonic turbojet engine was completed. In addition, a detailed thermodynamic, plasmadynamic, and electromagnetic analysis was combined to offer a single, comprehensive model to describe more fully the proper plasma flows and magnetic fields required for successful operation of the MHD energy bypass system.
The unique contribution of this research involved modeling the current density, temperature, velocity, pressure, electric field, Hall parameter, and electrical power throughout an annular MHD generator and an annular MHD accelerator taking into account an external magnetic field within a moving flow field, collisions of electrons with neutral particles in an ionized flow field, and collisions of ions with neutral particles in an ionized flow field (ion slip). In previous research, the ion slip term has not been considered.
The MHD energy-bypass system model showed that it is possible to expand the operating range of a supersonic jet engine from a maximum of Mach 3.5 to a maximum of Mach 7. The inclusion of ion slip within the analysis further showed that it is possible to 'drive' this system with maximum magnetic fields of 3 T and with maximum conductivity levels of 11 mhos/m. These operating parameters better the previous findings of 5 T and 10 mhos/m, and reveal that taking into account collisions between ions and neutral particles within a weakly ionized flow provides a more realistic model with added benefits of lower magnetic fields and conductivity levels especially at the higher Mach numbers. (Abstract shortened by UMI.)
Moreira, Farney Coutinho. « On the behavior of upwind schemes applied to three-dimensional supersonic and hypersonic cold gas flow simulations of aerospace configurations ». Instituto Tecnológico de Aeronáutica, 2007. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=397.
Texte intégralRedding, Jeremy. « Deformation, Fragmentation and Vaporization of Volatile Liquid Droplets in Shock-Laden Environments ». University of Cincinnati / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1613745275535815.
Texte intégralBurym, A. S. « Development of the newest supersonicaircraft ». Thesis, Київський національний університет технологій та дизайну, 2018. https://er.knutd.edu.ua/handle/123456789/11430.
Texte intégralFojtl, Michal. « Výpočet aerodynamických charakteristik nosiče pro nízkou oběžnou dráhu ». Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2017. http://www.nusl.cz/ntk/nusl-316914.
Texte intégralCrowell, 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.
Texte intégralWallis, Scott Evan. « Innovative Transverse Jet Interaction Arrangements in Supersonic Crossflow ». Thesis, Virginia Tech, 2001. http://hdl.handle.net/10919/36041.
Texte intégralMaster of Science
Douay, Guy. « Modélisation et étude numérique de la turbulence compressible en écoulements supersoniques ». Rouen, 1994. http://www.theses.fr/1994ROUES002.
Texte intégralNoubel, Hugo. « Etude expérimentale du comportement aérodynamique et optimisation des performances des planeurs hypersoniques dans des écoulements supersoniques et hypersoniques raréfiés ». Electronic Thesis or Diss., Orléans, 2024. http://www.theses.fr/2024ORLE1001.
Texte intégralThe main objective of this thesis work is to experimentally characterize the impact of viscous effects on the aerodynamic performance of hypersonic gliders. The study includes six low-pressure flows (ranging from 0.068 Pa to 71.11 Pa) from the MARHy wind tunnel, four supersonic flows (Mach 2 and Mach 4), and two hypersonic flows (Mach 20). A total of 6 models were tested, aiming to study geometries with different degrees of optimization and to understand the impact of viscous effects one ach of them. Various diagnostics were used to carry out this study : Firstly, an aerodynamic balance was developed to measure the drag and lift forces of the different configurations. Next, shock waves were visualized using glow discharge imaging. Finally, a parietal pressure study was carried out on two hypersonic gliders. This thesis work establishes a broad experimental database on hypersonic gliders in the rarefied regime. Force studies have enabled us to quantify the evolution of glide ratio during atmospheric re-entry as a function of the degree of rarefaction (Tsien parameter). As far as angles of attack are concerned, formulations taking viscous effects into account have been established and can be used in the optimization of high-altitude waveriders. A hypersonic glider incorporating these data has been tested and shows promise at high altitude. Throughout this thesis, results have highlighted the impact of viscous effects on the aerodynamic performance of hypersonic gliders
Nieberding, Zachary J. « An Investigation of Acoustic Wave Propagation in Mach 2 Flow ». University of Cincinnati / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1406881591.
Texte intégralCoumar, Sandra. « Etude des mécanismes physiques induits pas un actionneur plasma appliqué au contrôle d’écoulements raréfiés super/hypersoniques dans le cadre de rentrées atmosphériques ». Thesis, Orléans, 2017. http://www.theses.fr/2017ORLE2025/document.
Texte intégralSpace missions are arousing renewed interest in these recent years. However, when coming to the entryinto the atmosphere, major issues are still to be considered. To answer this problem, a new Entry DescentLanding technique is proposed: plasma actuation to increase the drag force over the vehicle body and thus,decrease its speed. In this thesis, a plasma actuator is tested in three supersonic rarefied flows (N1(M2-8Pa), N2(M4-8Pa) and N3(M4-71Pa)) and a hypersonic one (M20-0.062Pa), all generated by the wind tunnelMARHy.The plasma actuator induces flow modifications over the studied model, such as a change in the shock waveshape and an increase in the shock wave angle. In order to better understand the phenomena governingthese modifications, Pitot pressure, surface and gas temperature, electron data and spectroscopicmeasurements were analyzed. The results shown that two types of effects are involved: thermal (bulk andsurface) and ionization. Moreover, it was demonstrated that these effects had not the same importancedepending on the flow conditions.The plasma actuator was also modified in order to improve it. In particular, two types of generators wereused to biase the cathode: DC and pulsed. Finally, it was shown that, for a discharge power of 80 W, a 13%increase in the drag force could be expected and thus, a decrease in the heat load over the model body ofmore than 25%. Therefore, plasma actuators seem to be promising applications for space missions andatmospheric entries
André, Thierry. « Contrôle actif de la transition laminaire-turbulent en écoulement hypersonique ». Thesis, Orléans, 2016. http://www.theses.fr/2016ORLE2022/document.
Texte intégralDuring a hypersonic flight (Mach 6, 20 km altitude), the boundary layer developing on the forebody of a vehicle is laminar. This state may destabilize the scramjet engine propelling the vehicle. To overcome this problem during the flight, the boundary layer transition has to be forced using a control device whose effect is fixed (passive) or adjustable (active). In this work, we analyze the efficiency of a jet in crossflow in forcing the boundary layer transition on a generic forebody. The flow is computed with a Large Eddy Simulations (LES) approach. A parametric study of the injection pressure allows the efficiency of the jet in tripping the boundary layer to be quantified. The influence of flight conditions (Mach, altitude) on the transition is also studied. Dynamic Mode Decomposition (DMD) is applied to the simulation results to determine the transition leading to dynamic modes and to understand underlying transition mechanisms. Experiments in the Purdue University quiet wind tunnel (BAM6QT) were performed to quantify the efficiency of a passive transition device (diamond roughnesses) and an active transition device (single air jet) in tripping the boundary layer. A thermo-sensitive paint and pressure transducers (Kulite, PCB) were used to determine the state of the boundary layer on the generic forebody. Experimental and numerical results show a sonic injection is sufficient to induce transition. We observe from the experiments that for the same penetration height, a single roughness is less efficient than a single air jet in destabilizing the boundary layer
劉台安. « On waverider shapes applied to future supersonic and hypersonic configuration ». Thesis, 1990. http://ndltd.ncl.edu.tw/handle/43529985420926245312.
Texte intégralMunuswamy, Nithiyaraj. « Jet Injection into Supersonic Crossflow : Flowfield and Mixing studies ». Thesis, 2018. https://etd.iisc.ac.in/handle/2005/4738.
Texte intégralJoarder, Ratan. « Demonstration Of Supersonic Combustion In A Combustion Driven Shock-Tunnel ». Thesis, 2009. https://etd.iisc.ac.in/handle/2005/1005.
Texte intégralJoarder, Ratan. « Demonstration Of Supersonic Combustion In A Combustion Driven Shock-Tunnel ». Thesis, 2009. http://hdl.handle.net/2005/1005.
Texte intégralZhikharev, Constantin N. « Interaction theory for hypersonic separation and supersonic flow past a flexible wall / ». Diss., 1999. http://gateway.proquest.com/openurl?url_ver=Z39.88-2004&rft_val_fmt=info:ofi/fmt:kev:mtx:dissertation&res_dat=xri:pqdiss&rft_dat=xri:pqdiss:9935191.
Texte intégralHou, Chang-Huan, et 侯昌桓. « A Study of Supersonic, Transonic, and Hypersonic Small Perturbation Theory and Their Verifications ». Thesis, 1999. http://ndltd.ncl.edu.tw/handle/20199326053444391078.
Texte intégral淡江大學
航空太空工程學系
87
The essential point of view in this paper is to re-examine the small perturbation theory of supersonic, transonic, and hypersonic flow. The asymptotic solutions of boundary value problems of centered expansion and compression waves for supersonic, transonic, and hypersonic nonlinear small disturbance equations are exhibited. The asymptotic solution of compression wave is verified by the exact solution of the oblique shock wave theory. Due to the singularity at the corner, the supersonic linearized theory is invalid for calculating the flow field of corner flow. By using the method of strained coordinates, the nonlinear asymptotic theory of supersonic flow is built and it gives the correct solution for corner flow. The shock wave position and the pressure coefficient on the wedge for supersonic, transonic, and hypersonic small disturbance theory are given to the first order; and the results agree well with first order asymptotic solution of the exact solution of the oblique shock wave theory. Keywords : supersonic, transonic, and hypersonic nonlinear small disturbance theory, corner flow, oblique shock wave theory
Chen, Yang Shie, et 楊士震. « The Study of Internal and External Compressible Viscous Flow for Supersonic and Hypersonic ». Thesis, 1993. http://ndltd.ncl.edu.tw/handle/11663006880731778965.
Texte intégral(6632393), Ian Avalon Hall. « Simulating Scramjet Behavior : Unstart Prediction in a Supersonic, Turbulent Inlet-Isolator Duct Flow ». Thesis, 2019.
Trouver le texte intégralLee, Sung-Wei, et 李嵩蔚. « A Study of Nonlinear Theories of Supersonic, Transonic, and Hypersonic Flow in Far Field and Whole Field ». Thesis, 2002. http://ndltd.ncl.edu.tw/handle/32102230248654132219.
Texte intégral淡江大學
航空太空工程學系
90
The essential point of view in this paper is to re-examine the small perturbation theories of supersonic, transonic, and hypersonic flow in the far field and whole field. Due to the singularity at the corner, the supersonic linearized theory is invalid for calculating the flow field of corner flow. By using the method of strained coordinates, the nonlinear theory of supersonic flow is built and it gives the correct solution for the whole field of corner flow. By using the asymptotic expansion, a systematic and rigorous approach for obtaining the supersonic nonlinear far field equation ( inviscid Burgers equation ) is exhibited. The transonic and hypersonic far field equations are derived from the supersonic far field equation by considering a general expansion of free stream Mach number in terms of transonic and hypersonic similarity parameters together with stretched coordinates. The asymptotic solution of the boundary-value problem of corner flow are obtained from the nonlinear theories of supersonic, transonic, and hypersonic flow in far field and whole field. The far field and whole field results of supersonic, transonic, and hypersonic corner flow are also verified in the physical coordinates and far field coordinates respectively. It is worth mentioning that the mathematical structures of the far field and whole field equations of the supersonic flow are similar in the physical coordinates, but they are quite different in the far field coordinates. The problem of the supersonic, transonic, and hypersonic flow past a parabolic-shaped airfoil are solved in the far field including the similar structure of leading and trailing curved shocks.
Devaraj, Manoj Kumar K. « Physical insights into unstart dynamics of a hypersonic mixed compression intake ». Thesis, 2021. https://etd.iisc.ac.in/handle/2005/5655.
Texte intégralTichenor, Nathan R. « Characterization of the Influence of a Favorable Pressure Gradient on the Basic Structure of a Mach 5.0 High Reynolds Number Supersonic Turbulent Boundary Layer ». 2010. http://hdl.handle.net/1969.1/ETD-TAMU-2010-08-8407.
Texte intégralGriffiths, Alan David. « Development and demonstration of a diode laser sensor for a scramjet combustor ». Phd thesis, 2005. http://hdl.handle.net/1885/47106.
Texte intégralMahapatra, Debabrata. « Investigation Of Ramp/Cowl Shock Interaction Processes Near A Generic Scramjet Inlet At Hypersonic Mach Number ». Thesis, 2008. https://etd.iisc.ac.in/handle/2005/807.
Texte intégralMahapatra, Debabrata. « Investigation Of Ramp/Cowl Shock Interaction Processes Near A Generic Scramjet Inlet At Hypersonic Mach Number ». Thesis, 2008. http://hdl.handle.net/2005/807.
Texte intégral(11355756), Jonathan J. Gaskins. « The Effect of Near Wall Disturbances on a Compressible Turbulent Boundary Layer ». Thesis, 2021.
Trouver le texte intégralMaity, Arnab. « Optimal Guidance Of Aerospace Vehicles Using Generalized MPSP With Advanced Control Of Supersonic Air-Breathing Engines ». Thesis, 2012. https://etd.iisc.ac.in/handle/2005/2550.
Texte intégralMaity, Arnab. « Optimal Guidance Of Aerospace Vehicles Using Generalized MPSP With Advanced Control Of Supersonic Air-Breathing Engines ». Thesis, 2012. http://etd.iisc.ernet.in/handle/2005/2550.
Texte intégralKotnala, Sourabh. « Lattice Boltzmann Relaxation Scheme for Compressible Flows ». Thesis, 2012. http://etd.iisc.ac.in/handle/2005/3257.
Texte intégral