Relevant bibliographies by topics / Combustion and propulsion

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Combustion and propulsion'

Author: Grafiati
Published: 3 June 2025
Last updated: 31 July 2025

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Journal articles on the topic "Combustion and propulsion"

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ORKISZ, Marek, Piotr WYGONIK, Michał KUŹNIAR, and Maciej KALWARA. "Comparative analysis of combustion engine and hybrid propulsion unit in aviation application in terms of emission of harmful compounds in the exhausts emitted to the atmosphere." Combustion Engines 178, no. 3 (2019): 213–17. http://dx.doi.org/10.19206/ce-2019-337.

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Comparative analysis of combustion and hybrid propulsion unit in aviation application in terms of emission of harmful compounds in the exhausts emitted to the atmosphere. For the propulsion of the AOS 71 motor glider, two types of propulsion were planned as de-velopment versions. The first analysed propulsion is based on a combustion engine, but of the Wankel type (LCR 814 engine with the power of 55 kW). The second designed propulsion is an hybrid based on a LCR 407 combustion engine with a power of 28 kW, which is connected in series with an electric generator propelling the engine (Emrax 22
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LeCren, R. T., R. E. Gildersleeve, and R. A. Swanek. "Combustor and Seal System for a Water Piston Propulsor." Journal of Engineering for Gas Turbines and Power 111, no. 1 (1989): 117–22. http://dx.doi.org/10.1115/1.3240206.

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The Water Piston Propulsor (WPP) is an advanced in-water propulsion system for Marine Corps amphibious vehicles. Significant weight and volume reductions are the primary advantages of the WPP system versus the more conventional propulsion technologies used today. WPP thrust is produced by porting high-pressure combustion gases into the water-filled channels of a rotor. Gas expansion results in the expulsion of water from the downstream end of the rotor channel. Solar Turbines Incorporated, a subsidiary of Caterpillar Inc., is currently under contract to the David Taylor Research Center for the
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Fureby, C. "Large eddy simulation modelling of combustion for propulsion applications." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 367, no. 1899 (2009): 2957–69. http://dx.doi.org/10.1098/rsta.2008.0271.

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Predictive modelling of turbulent combustion is important for the development of air-breathing engines, internal combustion engines, furnaces and for power generation. Significant advances in modelling non-reactive turbulent flows are now possible with the development of large eddy simulation (LES), in which the large energetic scales of the flow are resolved on the grid while modelling the effects of the small scales. Here, we discuss the use of combustion LES in predictive modelling of propulsion applications such as gas turbine, ramjet and scramjet engines. The LES models used are described
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Duan, Runze, Yifan Cao, Hongbin Duan, et al. "Effect of the inner-surface baffles on the tangential acoustic mode in the cylindrical combustor." Open Physics 18, no. 1 (2020): 1215–22. http://dx.doi.org/10.1515/phys-2020-0187.

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Abstract The combustion instability in a propulsion system is a ubiquitous problem. The radial baffles usually installed on the injector faceplate eliminate the combustion instability (acoustic pressure oscillation) in the propulsion system. In this article, the longitudinal baffles are installed on the inner surface of the combustor wall to control the combustion instabilities. The first-order and second-order tangential modes are induced in the experiments. The effects of the parameters of the baffle on the acoustic pressure oscillation in the cylindrical combustor are investigated. The effe
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Pandey, K. M., and Pinku Debnath. "Review on Recent Advances in Pulse Detonation Engines." Journal of Combustion 2016 (2016): 1–16. http://dx.doi.org/10.1155/2016/4193034.

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Pulse detonation engines (PDEs) are new exciting propulsion technologies for future propulsion applications. The operating cycles of PDE consist of fuel-air mixture, combustion, blowdown, and purging. The combustion process in pulse detonation engine is the most important phenomenon as it produces reliable and repeatable detonation waves. The detonation wave initiation in detonation tube in practical system is a combination of multistage combustion phenomena. Detonation combustion causes rapid burning of fuel-air mixture, which is a thousand times faster than deflagration mode of combustion pr
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Rao, M. Srinivasa. "Flow Analyses of Integrated Liquid Fuel RAMJET Propulsion System." Defence Science Journal 74, no. 2 (2024): 288–92. http://dx.doi.org/10.14429/dsj.74.18510.

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A CFD study is performed to check the seamless flow behaviour of the Liquid Fuel Ramjet Propulsion system which includes, air intakes, combustor and nozzle. Resolving both supersonic and subsonic flow scales in the same domain makes the simulations complex. Addition of combustion with stiff chemistry makes the simulations more difficult. CFD simulations are carried out using commercially available CFD software. Liquid fuel is injected as discrete phase and the flow turbulence is modelled using Realizable k-ε turbulence model. Jet-A + air combustion has been simulated using combined finite rate
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Stalker, R. J., and A. Paull. "Experiments on cruise propulsion with a hydrogen scramjet." Aeronautical Journal 102, no. 1011 (1998): 37–44. http://dx.doi.org/10.1017/s0001924000065726.

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AbstractMeasurements of drag have been made, in a shock tunnel, on a simple integrated vehicle-engine combination for hypersonic cruise with hydrogen scramjet propulsion. The test flow Mach number was 6·4, and the velocity was 2·45 kms-1. Zero drag, which is the necessary condition for cruise, was achieved as the equivalence ratio approached one. It was found that an analysis using established aerodynamic concepts was adequate for predicting drag in the case of no combustion. When combustion occurred results of direct connect experiments provided a qualitative guide to the measured levels of d
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Biró, Norbert, and Péter Kiss. "Emission Quantification for Sustainable Heavy-Duty Transportation." Sustainability 15, no. 9 (2023): 7483. http://dx.doi.org/10.3390/su15097483.

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Vehicles equipped with internal combustion engines (ICE) are major contributors to greenhouse gas (GHG) emissions and dependence on fossil fuels. Alternatives such as electric, hydrogen fuel cell and biofuel-based propulsions are being considered as a replacement for the well-established ICE vehicles to reduce GHG emissions and provide sustainable transportation. This paper will compare various heavy-duty vehicle (HDV) propulsion combinations using a well-to-wheel (WTW) analysis, separated into two parts: Well-to-Tank (WTT) and Tank-to-Wheel (TTW). The WTW analysis of ICE HDV is based on a Eur
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Kinoshita, Y., J. Kitajima, Y. Seki, and A. Tatara. "Experimental Studies on Methane-Fuel Laboratory Scale Ram Combustor." Journal of Engineering for Gas Turbines and Power 117, no. 3 (1995): 394–400. http://dx.doi.org/10.1115/1.2814108.

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The laboratory scale ram combustor test program has been investigating fundamental combustion characteristics of a ram combustor, which operates from Mach 2.5 to 5 for the super/hypersonic transport propulsion system. In our previous study, combustion efficiency had been found poor, less than 70 percent, due to a low inlet air temperature and a high velocity at Mach 3 condition. To improve the low combustion efficiency, a fuel zoning combustion concept was investigated by using a subscale combustor model first. Combustion efficiency more than 90 percent was achieved and the concept was found v
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Nikolayev, O. D., I. D. Bashliy, D. V. Klymenko, and N. V. Khoriak. "Interaction of the acoustic oscillations of the combustion products in the chamber of a propulsion system with structural vibrations." Technical mechanics 2025, no. 1 (2025): 28–35. https://doi.org/10.15407/itm2025.01.028.

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The most critical operating conditions of propulsion system chambers are often due to the development of dynamic processes characterized by excess values of operational parameters. Pressure surges and a sharp increase in the local temperature of the combustion products may result in a structural failure of the combustion chamber and a critical behavior of the propulsion system, to the point of combustion termination. An approach was developed to solving problems of propulsion system dynamics – assessment of the effect of the acoustic oscillations of the combustion products in the chamber with
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Dissertations / Theses on the topic "Combustion and propulsion"

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Gete, Zenebe. "et-enhanced turbulent combustion." Thesis, University of British Columbia, 1991. http://hdl.handle.net/2429/29969.

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A study of the squish-jet design concept in spark ignition engines, with central ignition, was conducted in a constant volume chamber. The effects of jet size, jet number and jet orientation in generating turbulence and jet enhanced turbulent combustion were investigated. Three sets of configurations with three port sizes were used in this study. The research was carried out in three stages: 1.Qualitative information was obtained from flow visualization experiments via schlieren photography at 1000 frames per second. The flow medium was air. A sequence of frames at specific time intervals wer
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Eugênio, Ribeiro Fábio Henrique. "Numerical Simulation of Turbulent Combustion in Situations Relevant to Scramjet Engine Propulsion." Thesis, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique, 2019. http://www.theses.fr/2019ESMA0001/document.

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Les super-statoréacteurs sont des systèmes de propulsion aérobie à grande vitesse qui ne nécessitent pas d’éléments rotatifs pour comprimer l’écoulement d’air. Celui-ci est comprimé dynamiquement par un système d’admission intégré dans le véhicule, atteignant la pression et la température requises pour que la combustion puisse s’opérer dans la chambre de combustion. La chambre de combustion est traversée par un écoulement supersonique dans ce type de moteur, ce qui limite considérablement le temps disponible pour injecter le carburant, le mélanger avec un oxydant, enflammer le mélange obtenu e
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Eagle, Walter Ethan. "Modeling of a high energy density combustion based aluminum and steam propulsion system." College Park, Md.: University of Maryland, 2007. http://hdl.handle.net/1903/7813.

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Thesis (M.S.) -- University of Maryland, College Park, 2007.<br>Thesis research directed by: Dept. of Aerospace 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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Michalski, Quentin. "Étude expérimentale de la combustion à volume constant pour la propulsion aérobie : influence de l'aérodynamique et de la dilution sur l'allumage et la combustion." Thesis, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique, 2019. http://www.theses.fr/2019ESMA0009/document.

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Les turbomachines actuelles ont atteint un niveau de maturité technique très élevé. De nouvelles architectures reposant sur des cycles thermodynamiques basés sur une combustion à gain de pression, comme la combustion à volume constant (CVC), ont le potentiel d’augmenter leur efficacité. Dans cette étude,une solution qui repose sur l’intégration dans une turbomachine de chambres de combustion à volume constant sans piston (CVCSP) est considérée. Les objectifs de ces travaux de thèse sont doubles : dans un premier temps de développer et de caractériser extensivement un nouveau dispositif (CV2) d
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Garby, Romain. "Simulations of flame stabilization and stability in high-pressure propulsion systems." Phd thesis, Toulouse, INPT, 2013. http://oatao.univ-toulouse.fr/9706/1/garby.pdf.

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Braconnier, Alexandre. "Étude expérimentale de la combustion d’une particule d’aluminium isolée : influence de la pression et de la composition de l’atmosphère oxydante." Thesis, Orléans, 2020. http://www.theses.fr/2020ORLE3140.

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Les poudres d'aluminium possèdent des propriétés énergétiques intéressantes et sont couramment intégrées à la composition de certains propergols solides pour améliorer les performances des systèmes de propulsion. Néanmoins, la présence d’une phase dispersée au sein de l'écoulement propulsif peut altérer la stabilité des moteurs à propergol solide (MPS) et l'utilisation du potentiel énergétique des particules d'aluminium nécessite d'être optimisée pour accroître davantage le rendement moteur. Des enjeux majeurs sont alors associés à la modélisation du processus réactionnel des gouttes afin d’am
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Villenave, Nicolas. "Étude expérimentale des propriétés fondamentales de la combustion de l'hydrogène pour des applications de propulsion." Electronic Thesis or Diss., Orléans, 2025. http://www.theses.fr/2025ORLE1001.

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En vue d'atteindre la neutralité carbone d'ici 2050, l’Union européenne envisage l'hydrogène comme un vecteur énergétique prometteur afin de réduire la consommation des ressources fossiles. Alors que les piles à combustible et les véhicules électriques occupent déjà une place importante dans la décarbonation du secteur des transports, l'hydrogène est également considéré comme une alternative aux carburants conventionnels pour les véhicules lourds. Toutefois, de nombreux obstacles liés aux propriétés physico-chimiques ainsi qu’à la combustion pauvre en hydrogène sont encore à l’étude : appariti
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Airiau, Magdeleine. "Analyse d'images expérimentales par apprentissage profond pour la caractérisation de la combustion de l'aluminium en propulsion solide." Electronic Thesis or Diss., université Paris-Saclay, 2024. http://www.theses.fr/2024UPASG062.

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L'aluminium est ajouté à la composition du propergol solide afin d'augmenter les performances propulsives d'environ 10%, mais peut aussi entraîner des phénomènes néfastes tels que des instabilités thermo-acoustiques conduisant à des oscillations de pression. La caractérisation de l'aluminium en combustion au-dessus de la surface du propergol est donc essentielle pour étudier la stabilité d'un moteur fusée. De nombreux travaux de recherche ont été réalisés pour prédire ces instabilités par le calcul. Cependant, ces modèles numériques manquent de données d'entrées précises, telles que la taille
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Zahn, Alexander R. "Characterization and Examination of Performance Parameters of a Back-pressurized RDC." University of Cincinnati / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1554119639742205.

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Rock, Christopher. "Experimental Studies of Injector Array Configurations for Circular Scramjet Combustors." Diss., Virginia Tech, 2010. http://hdl.handle.net/10919/77208.

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A flush-wall injector model and a strut injector model representative of state of the art scramjet engine combustion chambers were experimentally studied in a cold-flow (non-combusting) environment to determine their fuel-air mixing behavior under different operating conditions. The experiments were run at nominal freestream Mach numbers of 2 and 4, which simulates combustor conditions for nominal flight Mach numbers of 5 and 10. The flush-wall injector model consists of sixteen inclined, round, sonic injectors distributed around the wall of a circular duct. The strut injector model has sixtee
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Books on the topic "Combustion and propulsion"

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D, Roy G., ed. Propulsion combustion: Fuels to emissions. Taylor & Francis, 1998.

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J, Priem Richard, and United States. National Aeronautics and Space Administration., eds. Analysis of 5 KHz combustion instabilities in 40K methane/LOX combustion chambers. National Aeronautics and Space Administration, 1988.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Combustion instabilities in liquid-fuelled propulsion systems. AGARD, 1989.

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L, Bulzan Daniel, and United States. National Aeronautics and Space Administration., eds. On the combustion of a laminar spray. National Aeronautics and Space Administration, 1993.

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K, Kuo Kenneth, and Hori Keiichi, eds. Advancements in energetic materials and chemical propulsion. Begell House, 2008.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Hypersonic combined cycle propulsion. AGARD, 1990.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Hypersonic combined cycle propulsion. AGARD, 1990.

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United States. National Aeronautics and Space Administration., ed. Axisymmetric single shear element combustion instability experiment. National Aeronautics and Space Administration, 1993.

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D, Roy G., ed. Combustion processes in propulsion: Control, noise, and pulse detonation. Elsevier Butterworth/Heinemann, 2006.

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Center, NASA Glenn Research, ed. Comparison of Mars aircraft propulsion systems. National Aeronautics and Space Administration, Glenn Research Center, 2003.

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Book chapters on the topic "Combustion and propulsion"

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Bruno, Claudio. "Combustion." In Airbreathing Hypersonic Propulsion. Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-7927-9_6.

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Culick, F. E. C. "Combustion Instabilities in Propulsion Systems." In Unsteady Combustion. Springer Netherlands, 1996. http://dx.doi.org/10.1007/978-94-009-1620-3_9.

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Babu, V. "Basics of Combustion Thermodynamics." In Fundamentals of Propulsion. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-79945-8_4.

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Glaskova, A. P. "Catalytic Combustion Processes." In Modern Research Topics in Aerospace Propulsion. Springer New York, 1991. http://dx.doi.org/10.1007/978-1-4612-0945-4_5.

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Rashkovskiy, Sergey A., Yury M. Milyokhin, and Alexander V. Fedorychev. "Combustion of Solid Propellants with Energetic Binders." In Chemical Rocket Propulsion. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27748-6_16.

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Babuk, Valery A. "Formulation Factors and Properties of Condensed Combustion Products." In Chemical Rocket Propulsion. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27748-6_13.

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Saini, Rohit, Ashoke De, and S. Gokulakrishnan. "Direct Numerical Simulation Study of Lean Hydrogen/Air Premixed Combustion." In Energy for Propulsion. Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-10-7473-8_11.

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Hampp, Fabian, and Rune Peter Lindstedt. "Quantification of External Enthalpy Controlled Combustion at Unity Damköhler Number." In Energy for Propulsion. Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-10-7473-8_8.

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Weiser, Volker, Andrea Franzin, Luigi T. DeLuca, et al. "Combustion Behavior of Aluminum Particles in ADN/GAP Composite Propellants." In Chemical Rocket Propulsion. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27748-6_10.

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Culick, F. E. C. "Combustion Instabilities and Rayleigh’s Criterion." In Modern Research Topics in Aerospace Propulsion. Springer New York, 1991. http://dx.doi.org/10.1007/978-1-4612-0945-4_8.

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Conference papers on the topic "Combustion and propulsion"

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Inamura, Takao, Mikihiro Sei, Mamoru Takahashi, and Akinaga Kumakawa. "Combustion characteristics of ramjet combustor." In 32nd Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-2665.

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TAMURA, HIROSHI, FUMIEI ONO, AKINAGA KUMAKAWA, and NOBUYUKI YATSUYANAGI. "LOX/methane staged combustion rocket combustor investigation." In 23rd Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-1856.

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SCHADOW, K., E. GUTMARK, and K. WILSON. "Active combustion control in a coaxial dump combustor." In 26th Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-2447.

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Lemcherfi, Aaron I., Rohan Gejji, Tristan L. Fuller, William E. Anderson, and Carson D. Slabaugh. "Investigation of Combustion Instabilities in a Full Flow Staged Combustion Model Rocket Combustor." In AIAA Propulsion and Energy 2019 Forum. American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-3948.

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BALLAL, D., and T. CHEN. "Turbulence-combustion interaction in practical combustion systems." In 22nd Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-1607.

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ZUKOSKI, E. "Combustion instability sustained by unsteady vortex combustion." In 21st Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-1248.

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Culick, F. "Combustion instabilities - Mating dance of chemical, combustion, and combustor dynamics." In 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-3178.

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SCHADOW, K., E. GUTMARK, K. WILSON, and R. SMITH. "Multi-step dump combustor design to reduce combustion instabilities." In 24th Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-2854.

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JIANG, TSUNG, and WING-JER HSU. "Comparison of droplet combustion models in spray combustion." In 27th Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-2203.

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ATTYA, A., M. HABIB, and M. TAHA. "Combustion characteristics of gaseous flames in a gas turbine combustor." In 25th Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2892.

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Reports on the topic "Combustion and propulsion"

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Glassman, I. AASERT95/Science and Engineering Training in Combustion and Propulsion. Defense Technical Information Center, 1999. http://dx.doi.org/10.21236/ada359227.

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Chan, S. H., C. C. Tan, Y. G. Zhao, and P. J. Janke. Li-SF(6) Combustion in Stored Chemical Energy Propulsion Systems. Defense Technical Information Center, 1990. http://dx.doi.org/10.21236/ada224846.

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Yetter, Richard A., Vigor Yang, and I. A. Aksay. An Integrated Ignition and Combustion System for Liquid Propellant Micro Propulsion. Defense Technical Information Center, 2008. http://dx.doi.org/10.21236/ada483413.

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Klein, James K. Propulsion and Power Rapid Response R&D Support. Task Order 0006: Engineering Research, Testing, and Technical Analyses of Advanced Propulsion Combustion Concepts, Mechanical Systems, Lubricants and Fuels: Mechanical Systems. Defense Technical Information Center, 2009. http://dx.doi.org/10.21236/ada501397.

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Tishkoff, J. M., M. A. Birkan, G. S. Roy, and S. G. Lekoudis. AFOSR/ONR Contractors' Meeting on Combustion Rocket Propulsion Diagnostics of Reacting Flow Held in Ann Arbor, Michigan on 19-23 June 1989. Defense Technical Information Center, 1989. http://dx.doi.org/10.21236/ada224411.

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Alwosheel, Abdulrahman, and Michael Samsu Koroma. Environmental Performance of Passenger Cars in the KSA: Comparison of Different Technologies via a Life Cycle Assessment Approach. King Abdullah Petroleum Studies and Research Center, 2024. https://doi.org/10.30573/ks--2024-dp69.

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Analyzing the environmental performance of alternative vehicle technologies in the current energy landscape of the Kingdom of Saudi Arabia (KSA) is very important given their expected role in future transportation systems. This study presents a comprehensive life cycle assessment (LCA) of sedans and sport utility vehicles (SUVs) powered by different propulsion systems to analyze their environmental performance in the KSA context. The LCA examines multiple impact categories, with a particular focus on global warming potential (GWP). The results reveal that hybrid electric vehicles (HEVs), fuel
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