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Dissertations / Theses on the topic 'Supersonic nozzle'

Author: Grafiati

Published: 4 June 2021

Last updated: 26 July 2025

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1

Park, Yensil. "Heterogeneous Nucleation in a Supersonic Nozzle." The Ohio State University, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=osu1545323828317256.

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2

Haddad, A. "Supersonic nozzle design of arbitrary cross-section." Thesis, Cranfield University, 1988. http://hdl.handle.net/1826/3512.

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An investigation, both theoretical and experimental in nature, has been undertaken to develop a simple method for the design of supersonic nozzles and, indeed, inlets of quite complex shapes from known or calculated axisymmetric flowfields. 1he axisymmetric flowfield is determined using a computer program based on the method of characteristics. Streamlines are calculated by direct integration of the axisymmetric stream function. 7he desired shape is chosen at the exit of the computed axisymmetric nozzle having the desired length and Mach number. Its describing points are then traced along the

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3

Sartor, Raymond Francis. "A Theoretical Model of Supersonic Steam Nozzle Behavior /." The Ohio State University, 1996. http://rave.ohiolink.edu/etdc/view?acc_num=osu1487932351058977.

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4

Rajakuperan, E. "Experimental And Computational Investigations Of Underexpanded Jets From Elliptical Sonic Nozzles." Thesis, Indian Institute of Science, 1994. https://etd.iisc.ac.in/handle/2005/158.

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Three dimensional nozzles and jet flows have attracted the attention of many researchers due to their potential application to many practical devices. Rectangular nozzles are considered for short/vertical take off and landing aircrafts for achieving powered lift. Axisymmetric nozzles with lobes, tabs or slots and elliptical nozzles are considered for noise reduction in aircrafts and mixing augmentation in airbreathing rockets. Interaction of supersonic jets with solid surface, as in the case of retro and ullage rockets in launch vehicles and interaction of multiple jets as in the case of lau

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5

Rajakuperan, E. "Experimental And Computational Investigations Of Underexpanded Jets From Elliptical Sonic Nozzles." Thesis, Indian Institute of Science, 1994. http://hdl.handle.net/2005/158.

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Three dimensional nozzles and jet flows have attracted the attention of many researchers due to their potential application to many practical devices. Rectangular nozzles are considered for short/vertical take off and landing aircrafts for achieving powered lift. Axisymmetric nozzles with lobes, tabs or slots and elliptical nozzles are considered for noise reduction in aircrafts and mixing augmentation in airbreathing rockets. Interaction of supersonic jets with solid surface, as in the case of retro and ullage rockets in launch vehicles and interaction of multiple jets as in the case of laun

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6

Bhabhe, Ashutosh Shrikant. "Experimental Study of Condensation and Freezing in a Supersonic Nozzle." The Ohio State University, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=osu1343253869.

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7

Baier, Florian. "Noise Radiation from a Supersonic Nozzle with Jet/Surface Interaction." University of Cincinnati / OhioLINK, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1617108352134538.

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8

El, Mellouki Mohammed. "Numerical Study and Investigation of a Gurney Flap Supersonic Nozzle." Thesis, Mississippi State University, 2019. http://pqdtopen.proquest.com/#viewpdf?dispub=10979662.

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<p> Flow separation is a common fluid dynamics phenomenon that occurs within supersonic nozzles while operating at off-design pressures. Typically, off-design pressures result in a shock formation that leads to a non-uniformity of the exiting flow and creates flow separation and flow recirculation. So far, no effective solution has been presented to eliminate flow separation and increase the total performance of the nozzle. The purpose of this work is to investigate whether a Gurney flap may beneficially affect the exiting flow pattern. For a better understanding of the Gurney flap effect, thi

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9

Kirk, Daniel Robert 1975. "Aeroacoustic measurement and analysis of transient supersonic hot nozzle flows." Thesis, Massachusetts Institute of Technology, 1999. http://hdl.handle.net/1721.1/29883.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999.<br>Includes bibliographical references (p. 195-199).<br>A transient testing technique for the study of jet noise was investigated and assessed. A shock tunnel facility was utilized to produce short duration, 10-20 millisecond, under expanded supersonic hot air jets from a series of scaled nozzles. The primary purpose of the facility is to investigate noise suppressor nozzle concepts relevant to supersonic civil transport aircraft applications. The shock tube has many strengths; it is mechanically

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10

Robertson, Welsh Bradley. "On the influence of nozzle geometries on supersonic curved wall jets." Thesis, University of Manchester, 2017. https://www.research.manchester.ac.uk/portal/en/theses/on-the-influence-of-nozzle-geometries-on-supersonic-curved-wall-jets(bc8817e4-c812-44bc-8dfb-f5d0fdf62a72).html.

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Circulation control involves tangentially blowing air around a rounded trailing edge in order to augment the lift of a wing. The advantages of this technique over conventional mechanical controls are reduced maintenance and lower observability. Despite the technology first being proposed in the 1960s and well-studied since, circulation control is not in widespread use today. This is largely due to the high mass flow requirements. Increasing the jet velocity increases both the efficiency (in terms of mass flow) and effectiveness. However, as the jet velocity exceeds the speed of sound, shock st

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11

Soliman, Salah M. "Micro-Particles and Gas Dynamics in an Axi-Symmetric Supersonic Nozzle." University of Cincinnati / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1313772443.

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12

Barber, Matthew James. "Experimental investigation of normal, sonic injection through a wedge-shaped nozzle into supersonic flow." Thesis, This resource online, 1991. http://scholar.lib.vt.edu/theses/available/etd-08222009-040226/.

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13

KIM, Yongseok, and Yoshiaki NAKAMURA. "Effect of Nozzle Lip Shape on Screech Tone in a Supersonic Jet." 日本航空宇宙学会, 2008. http://hdl.handle.net/2237/13881.

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14

Wu, Jie [Verfasser]. "Boundary-layer Instability Experiments in a Tandem Nozzle Supersonic Wind Tunnel / Jie Wu." Aachen : Shaker, 2015. http://d-nb.info/106904864X/34.

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15

Wang, Peng C. "Large eddy simulation of high speed convergent-divergent nozzle flows." Thesis, Loughborough University, 2013. https://dspace.lboro.ac.uk/2134/11937.

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Interest in developing a detailed understanding of jet plume aerodynamics has increased significantly in recent years, for both civil (noise reduction) and military (Infra-Red signature modelling) aerospace applications. Such flows are critically dependent on turbulence modelling of the jet plume shear layer mixing. Reynolds averaged Navier Stokes (RANS) CFD tends to overpredict while Large Eddy Simulation (LES) CFD underpredicts potential core length. Difficulties in LES begin with the challenge of providing accurate resolution of thin turbulent boundary layers at nozzle exit. Providing physi

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16

Östlund, Jan. "Supersonic flow separation with application to rocket engine nozzles." Doctoral thesis, KTH, Mechanics, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3793.

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<p>The increasing demand for higher performance in rocketlaunchers promotes the development of nozzles with higherperformance, which basically is achieved by increasing theexpansion ratio. However, this may lead to flow separation andensuing instationary, asymmetric forces, so-called side-loads,which may present life-limiting constraints on both the nozzleitself and other engine components. Substantial gains can bemade in the engine performance if this problem can be overcome,and hence different methods of separation control have beensuggested. However, none has so far been implemented in full

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17

Xiao, Ruiyang. "The Freezing of Highly Sub-cooled H2O/D2O Droplets." The Ohio State University, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=osu1211567463.

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18

Ogunronbi, Kehinde Emeka. "Investigating the Phase Transitions of lower n-alkanes – pentane, hexane, and heptane - in a supersonic nozzle." The Ohio State University, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=osu1562608990281475.

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19

MOHAMED, ASHRAF ELSAID. "An Experimental Investigation of Supersonic Rectangular Over-Expanded Nozzle of Single and Two-Phase Flows." University of Cincinnati / OhioLINK, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1204661977.

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20

Jegede, Olaseinde. "Dual-axis fluidic thrust vectoring of high-aspect ratio supersonic jets." Thesis, University of Manchester, 2016. https://www.research.manchester.ac.uk/portal/en/theses/dualaxis-fluidic-thrust-vectoring-of-highaspect-ratio-supersonic-jets(6d6a5867-8281-4dfd-ac45-105ff4e73e39).html.

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A dual-axis fluidic thrust vectoring (FTV) system is proposed where the supersonic propulsive jet of an aircraft is exhausted over a scarfed (swept), curved surface to produce flight control moments in both the pitch and yaw axes. This work contributes towards practical dual-axis FTV through expansion of fundamental curved-wall jet (CWJ) understanding, development of the novel Superimposed Characteristics technique for supersonic nozzle design, and performance evaluation of an experimental scarfed curved wall FTV configuration. Previous work has suggested that the use of a sheared exhaust velo

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21

Glawe, Diana Dawn. "The Effects of Nozzle Geometry on Injection From The Base of a Strut Into Supersonic Flow /." The Ohio State University, 1995. http://rave.ohiolink.edu/etdc/view?acc_num=osu1487929745335373.

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22

Abdelhafez, Ahmed. "Effect of swirl on the choking criteria, shock structure, and mixing in underexpanded supersonic nozzle airflows." College Park, Md.: University of Maryland, 2009. http://hdl.handle.net/1903/9196.

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Thesis (Ph. D.) -- University of Maryland, College Park, 2009.<br>Thesis research directed by: Dept. of Mechanical Engineering. Title from t.p. of PDF. Includes bibliographical references. Published by UMI Dissertation Services, Ann Arbor, Mich. Also available in paper.

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23

Algattus, Said S. "Experimental investigation of noise reduction in supersonic jets due to jet rotation and to nozzle geometry changes." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1999. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape9/PQDD_0019/NQ43583.pdf.

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24

Coltrin, Ian S. "The Influence of Nozzle Spacing and Diameter on the Acoustic Emissions of Closely Spaced Supersonic Jet Arrays." BYU ScholarsArchive, 2012. https://scholarsarchive.byu.edu/etd/2935.

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The acoustic emissions from supersonic jets represent an area of significant research needs; not only in the field of aero-acoustics, but in industry as well where high pressure let down processes have been known to cause acoustically induced vibrations. A common method to reduce the acoustic emissions of such processes involves dividing the single larger supersonic flow into several smaller ones. Though this is common practice, there is not yet a current model which describes the reduction of acoustic emissions from an array of smaller supersonic jets. Current research which studies supersoni

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25

Stack, Cory M. "Turbulence Mechanisms in a Supersonic Rectangular Multistream Jet with an Aft-Deck." The Ohio State University, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=osu1560352886647369.

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26

Lilienberg, László. "Experimental loss measurements in an annular sector cascade at supersonic exit velocities." Thesis, KTH, Kraft- och värmeteknologi, 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-179902.

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Efficiency improvement is one of the most important aspects of engineering and especially important in the field of energy production. In the past decades, energy was mostly produced by fossil based technologies involving turbomachines, and the efficiency of these machines nearly quadrupled since the introduction of the first economically viable gas turbines. The progress continues, as there are still areas where improvement can be made. Such area is the High Pressure Turbine stage (HPT), which influences the flow characteristics and losses downstream, which this thesis will examine in more de

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27

Mullen, Christopher. "Radical-molecule reaction dynamics studied using a pulsed supersonic Laval nozzle flow reactor between 53 and 188 Kelvin." Diss., The University of Arizona, 2004. http://hdl.handle.net/10150/280633.

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A pulsed supersonic Laval nozzle flow reactor has been employed to investigate a variety of neutral-radical reaction processes at temperatures between 53 and 188 Kelvin. These supersonic flows simulate the conditions found in the Earth's upper atmosphere as well as certain environments in the interstellar medium and outer planetary atmospheres and thus provide direct information on the chemistry and physical processes occurring in those environments. Studies of this type, in the limit of 0 Kelvin, coupled with modern astronomical observations of planetary atmospheres and dense molecular clouds

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28

Retaureau, Ghislain J. "On recessed cavity flame-holders in supersonic cross-flows." Diss., Georgia Institute of Technology, 2012. http://hdl.handle.net/1853/43703.

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Flame-holding in a recessed cavity is investigated experimentally in a Mach 2.5 preheated cross-flow for both stable and unstable combustion, with a relatively low preheating. Self-sustained combustion is investigated for stagnation pressures and temperatures reaching 1.4 MPa and 750 K. In particular, cavity blowout is characterized with respect to cavity aspect ratio (L/D =2.84 - 3.84), injection strategy (floor - ramp), aft ramp angle (90 deg - 22.5 deg) and multi-fuel mixture (CH₄-H₂ or CH₄-C₂H₄ blends). The results show that small hydrogen addition to methane leads to significant increase

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29

Pathak, Harshad. "Nucleation and Droplet Growth During Co-condensation of Nonane and D₂O in a Supersonic Nozzle." The Ohio State University, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=osu1383312754.

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30

Chen, Ru-Ching. "Development of a Supersonic Nozzle and Test Section for use with a Magnetic Suspension System for Re-Entry Aeroshell Models." Case Western Reserve University School of Graduate Studies / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=case1544179612537658.

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31

Heiner, Mark C. "Development and Testing of a Hydrogen Peroxide Injected Thrust Augmenting Nozzle for a Hybrid Rocket." DigitalCommons@USU, 2019. https://digitalcommons.usu.edu/etd/7630.

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During a rocket launch, the point at which the most thrust is needed is at lift-off where the rocket is the heaviest since it is full of propellant. Unfortunately, this is also the point at which rocket engines perform the most poorly due to the relatively high atmospheric pressure at sea level. The Thrust Augmenting Nozzle (TAN) investigated in this paper provides a solution to this dilemma. By injecting extra propellant into the nozzle but downstream of the throat, the internal nozzle pressure is raised and the thrust is increased, and the nozzle efficiency, or specific impulse is potentiall

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32

Montre, Trevor Allen. "Experimental Investigation of a 2-D Air Augmented Rocket: Effects of Nozzle Lip Thickness on Rocket Mixing and Entrainment." DigitalCommons@CalPoly, 2011. https://digitalcommons.calpoly.edu/theses/662.

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Cold-flow tests were performed using a simulated Air Augmented Rocket (AAR) operating as a mixer-ejector in order to investigate the effects of varied primary nozzle lip thickness on mixing and entrainment. The simulated primary rocket ejector was supplied with nitrogen at a maximum chamber stagnation pressure of 1712 psi, and maximum flow rate of 1.67 lbm/s. Secondary air was entrained from a plenum, producing pressures as low as 6.8 psi and yielding maximum stagnation pressure ratios as high as 160. The primary ejector nozzles each had an area ratio of approximately 20, yielding average prim

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33

Papp, John Laszlo. "SIMULATION OF TURBULENT SUPERSONIC SEPARATED BASE FLOWS USING ENHANCED TURBULENCE MODELING TECHNIQUES WITH APPLICATION TO AN X-33 AEROSPIKE ROCKET NOZZLE SYSTEM." University of Cincinnati / OhioLINK, 2000. http://rave.ohiolink.edu/etdc/view?acc_num=ucin962118912.

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34

Zebiri, Boubakr. "Étude numérique des interactions onde de choc / couche limite dans les tuyères propulsives Shock-induced flow separation in an overexpanded supersonic planar nozzle A parallel high-order compressible flows solver with domain decomposition method in the generalized curvilinear coordinates system Analysis of shock-wave unsteadiness in conical supersonic nozzles." Thesis, Normandie, 2020. http://www.theses.fr/2020NORMIR06.

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La nécessité d’une meilleure compréhension du mécanisme d’entrainement pour l’instabilité à basse fréquence observée dans un écoulement dans une tuyère sur-détendue a été discutée. Le caractère instable de l’onde de choc/couche limite reste un défi pratique important pour les problèmes des écoulements dans les tuyères. De plus, pour une couche limite turbulente incidente donnée, ce type d’écoulement présente généralement des mouvements de choc à basse fréquence plus élevées qui sont moins couplés aux échelles de temps de la turbulence en amont. Cela peut être bon du point de vue d’un expérimen

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35

Berchon, Luciano da Silva. "Estudo numérico da influência da geometria de bocais convergente-divergente em escoamentos supersônicos." reponame:Biblioteca Digital de Teses e Dissertações da UFRGS, 2016. http://hdl.handle.net/10183/149839.

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O comportamento do escoamento supersônico no interior de bocais convergente-divergente retangulares é investigado numericamente, comparando-se quatro bocais com diferentes seções divergentes, com a mesma razão de aspecto AR=1.14 e mesma relação áreas da saída e da garganta dos bocais NAR=1.43. Os bocais são submetidos a diferentes pressões de admissão do fluido de trabalho, mantendo-se a relação entre a pressão de admissão e de descarga constante NPR=5. As simulações consideram o escoamento em regime permanente, compressível, viscoso, com abordagem baseada na massa específica (abordagem acopla

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36

Yanson, Logan M. "Effects of Liquid Superheat on Droplet Disruption in a Supersonic Stream." Link to electronic thesis, 2005. http://www.wpi.edu/Pubs/ETD/Available/etd-042905-151247/.

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37

Marrion, Maynard. "Separation control in over-expanded supersonic nozzles." Thesis, University of Oxford, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.490110.

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Needle-free drug and vaccine delivery devices have been developed by the Department of Engineering Science at The University of Oxford in collaboration with PowderJect Pharmaceuticals plc. In them, micro-particles of pharmaceuticai agent are accelerated, by a supersonic flow of gas in a nozzle, to velocities sufficient for them to penetrate the outer layers of the skin. If the gas flow is over-expanded relative to the atmosphere to which it discharges, shock waves form inside the nozzle, which cause the flow to separate from the wall. The resulting gas-particle flow field is highly non-uniform

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38

Warren, Arthur H. "Propulsion system analysis for conceptual design : drag and losses of nozzles and mixed compression inlets /." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-07112009-040259/.

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39

Paci, Paolo. "Monitoring vapor phase concentration in supersonic flows." Link to electronic thesis, 2003. http://www.wpi.edu/Pubs/ETD/Available/etd-0428103-215650.

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Thesis (M.S.)--Worcester Polytechnic Institute.<br>Keywords: infrared spectroscopy; aerosols; nucleation; tunable diode laser; condensation; supersonic nozzles. Includes bibliographical references (p. 73-76).

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40

OTTONELLO, ANDREA. "Application of Uncertainty Quantification techniques to CFD simulation of twin entry radial turbines." Doctoral thesis, Università degli studi di Genova, 2021. http://hdl.handle.net/11567/1046507.

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L'argomento principale della tesi è l'applicazione delle tecniche di quantificazione dell'incertezza (UQ) alla simulazione numerica (CFD) di turbine radiali twin entry impiegate nella turbosovralimentazione automobilistica. Lo studio approfondito di questo tipo di turbomacchine è affrontato nel capitolo 3, finalizzato alla comprensione dei principali parametri che caratterizzano e influenzano le prestazioni fluidodinamiche delle turbine twin scroll. Il capitolo 4 tratta di una piattaforma per l'analisi UQ sviluppata internamente tramite il set di strumenti open source ‘Dakota’. La piattaform

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41

Dingilian, Kayane Kohar. "Homogeneous Nucleation of Carbon Dioxide (CO2) in Supersonic Nozzles." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1607019789125519.

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42

Sinha, Somnath. "Experimental And Modeling Study Of Condensation In Supersonic Nozzles." The Ohio State University, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=osu1217268763.

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43

Matloch, Roman. "Analýza nadzvukového proudění plynu v diferenciálně čerpané komoře elektronového mikroskopu." Master's thesis, Vysoké učení technické v Brně. Fakulta elektrotechniky a komunikačních technologií, 2013. http://www.nusl.cz/ntk/nusl-220123.

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This work describes briefly electron microscopy issue and physical model of fluid flow. Then presented diploma thesis will be describing analysis and evaluation of the impact of supersonic flow on the pressure and density in the path of the primary electron beam in the differential pumping chamber. For analysis, evaluation and examination of the issue will be used CAD and CAE (Computer Aided Engineering) programs. At the same time it will be developed a methodology of calculation applicable to supersonic flow in the low pressure system at ANSYS CFX.

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44

Newman, Aaron W. "The effect of superheat on liquid droplets in a supersonic freestream." Link to electronic version, 1999. http://www.wpi.edu/Pubs/ETD/Available/etd-051199-174419/unrestricted/thesis.pdf.

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45

Boccaletto, Luca. "Maîtrise du décollement de tuyère. Analyse du comportement d'une tuyère de type TOC et définition d'un nouveau concept : le BOCCAJET." Thesis, Aix-Marseille 1, 2011. http://www.theses.fr/2011AIX10012/document.

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Cette recherche s’articule en deux parties. L’objectif de la première partie est d’analyser par voie expérimentale et numérique la phénoménologie du décollement interne, dit décollement de jet (en regimes transitoire et établi) dans les tuyères supersoniques refroidies par film fluide. La deuxième partie porte sur la réinterprétation des concepts de tuyère existants pour aboutir à la proposition d’un nouveau dispositif de détente supersonique, qui offre une résistance accrue au décollement de jet. La première partie de cette thèse est basée sur l’analyse des résultats expérimentaux obtenus lor

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46

Hartawan, Laksmono Santoso. "Experimental Study of Methanol Condensation and Nucleation in Supersonic Nozzles." The Ohio State University, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=osu1282055155.

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47

Bekka, Nadir. "Problématique des phénomènes des ondes de choc dans les tuyères supersoniques et leur interaction avec la structure." Electronic Thesis or Diss., Evry-Val d'Essonne, 2014. http://www.theses.fr/2014EVRY0005.

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La problématique des charges latérales dans les tuyères propulsives des moteurs fusées reste un enjeu majeur pour l’industrie aérospatiale. Par ailleurs, le souci d’allègement de la masse d’ensemble du lanceur conduit à concevoir des tuyères de finesse croissante qui à leur tour peuvent poser des problèmes aéroélastiques. En effet, il est bien établi que lors des phases de démarrage et d’extinction des moteurs fusées, la structure interagit avec l’écoulement principal, conduisant ainsi à la génération des effets aéroélastiques qui peuvent amplifier davantage les charges latérales pouvant mettr

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48

Clark, Kylen D. "A Numerical Comparison of Symmetric and Asymmetric Supersonic Wind Tunnels." University of Cincinnati / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1447071393.

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49

Mullick, Kelley Anne. "Binary Nucleation of n-butanol and Deuterium Oxide Conducted in Supersonic Nozzles." The Ohio State University, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=osu1324247960.

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50

Bolgar, Istvan [Verfasser], Christian J. [Akademischer Betreuer] Kähler, Christian J. Gutachter] Kähler, and Rolf [Gutachter] [Radespiel. "On the performance increase of future space launchers: Investigations of buffeting, its reduction via passive flow control, and the Dual-Bell nozzle concept at trans- and supersonic flight conditions / Istvan Bolgar ; Gutachter: Christian J. Kähler, Rolf Radespiel ; Akademischer Betreuer: Christian J. Kähler ; Universität der Bundeswehr München, Fakultät für Luft- und Raumfahrttechnik." Neubiberg : Universitätsbibliothek der Universität der Bundeswehr München, 2019. http://nbn-resolving.de/urn:nbn:de:bvb:706-6871.

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