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Добірка наукової літератури з теми "Scramjet engine"

Автор: Grafiati
Опубліковано: 6 вересня 2023
Оновлено: 7 вересня 2023

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Статті в журналах з теми "Scramjet engine"

1

Jiang, Baohong. "Comprehensive Analysis of the Advanced Technologies for Scramjet." Highlights in Science, Engineering and Technology 43 (April 14, 2023): 137–49. http://dx.doi.org/10.54097/hset.v43i.7413.

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Scramjet is a kind of aspirated engine, where oxygen in the atmosphere is used as oxidant to react with fuel in fuel bunker. Structural components are used in the scramjet to generate shock waves at high speed to compress the high-speed air flow, and realize the deceleration and pressurization of the air flow, which is different from engines where air compressors are used. Technologies related to the scramjet power/fuel are presented, and the features related to this kind of engines are highlighted in this paper. The development process of the scramjets in the application field both home and abroad is overviewed. The problems involved with scramjets in hypersonic vehicle application, combined cycle power system, design of thermal protection structures and high temperature materials are discussed. The critical technologies of scramjets, i.e., tail nozzle, combustion chamber, air inlet, fuel selection etc. are identified. The features of hydrocarbon fuel and its application in hypersonic vehicles are summarized. And the progress of research of the relevant technologies and personal prospects for scramjets are briefly described.
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2

Smart, M. "Scramjets." Aeronautical Journal 111, no. 1124 (October 2007): 605–19. http://dx.doi.org/10.1017/s0001924000004796.

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Abstract The supersonic combustion ramjet, or scramjet, is the engine cycle most suitable for sustained hypersonic flight in the atmosphere. This article describes some of the challenges facing scramjet designers, and the methods currently used for the calculation of scramjet performance. It then reviews the HyShot 2 and Hyper-X flight programs as examples of how sub-scale flights are now being used as important steps towards the development of operational systems. Finally, it describes some recent advances in three-dimensional scramjets with application to hypersonic cruise and multi-stage access-to-space vehicles.
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3

Jin, Liang, Xian Yu Wu, Jing Lei, Li Yan, Wei Huang, and Jun Liu. "CFD Analysis of a Hypersonic Vehicle Powered by Triple-Module Scramjets." Applied Mechanics and Materials 390 (August 2013): 71–75. http://dx.doi.org/10.4028/www.scientific.net/amm.390.71.

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A numerical investigation has been carried out to study the longitudinal performance of a hypersonic airbreathing vehicle with highly integrated triple-module scramjets. CFD-Fastran is used to evaluate the aerodynamic performance of the vehicle at inlet-open scramjet unpowered mode, and a chemical reacting code ChemTur3D has been built to evaluate the propulsion performance of the triple-module engines at scramjet powered mode. The flow conditions for the calculations include variations of angle of attack at Mach 5.85 test point. The wall pressure and surface friction are integrated to calculate drag, lift and pitching moment coefficients to predict the combined aeropropulsive force and moment characteristics during engine operation. Finally, numerical results is compared with available ground test data to assess solution accuracy, and a preflight aerodynamic database of the vehicle could be built for the hypersonic flight experiments.
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4

Daren, Y., C. Tao, and B. Wen. "An idea of distributed parameter control for scramjet engines." Aeronautical Journal 111, no. 1126 (December 2007): 787–96. http://dx.doi.org/10.1017/s0001924000001901.

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AbstractScramjet engines are used under extreme temperatures and with wide range of Mach numbers from 3 to 8 or higher and have shown different control properties from other airbreathing engines. New control problems involving distributed parameter control have been found concerning investigations of the control of scramjet engines whose physical states are spatially interacted and whose governing equations are partial differential equations. The work of this paper is based on the application of distributed parameter control conception to study the control problems of scramjet engines with the aim of achieving the desirable design properties and increasing control reliability. A new control idea based on shape control theory is put forward to realise the distributed parameter control of scramjet engines with the preconditions of proper space dimension and frequency-domain simplification. Simulation results and theoretic analysis for an axisymmetric, wall-injection scramjet engine show the feasibility and validity of the control idea.
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5

Cheng, Feng, Shuo Tang, Dong Zhang, and Yi Li. "Quasi-One-Dimensional Modeling and Analysis of RBCC Dual-Mode Scramjet Engine." International Journal of Turbo & Jet-Engines 36, no. 2 (May 27, 2019): 195–206. http://dx.doi.org/10.1515/tjj-2017-0055.

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Abstract The quasi-one-dimensional method for the dual-mode scramjet (DMR) of the hypersonic RBCC powered vehicle was simplified in most of open researches. Furthermore, these simplified method can not fully capture the processes of wall heat transfer, changes in the boundary layer and the ratio of specific heat and the transonic flow in the reacting flow. Addressing this problem, we establish the models for processing core flow area, transonic flow and pre-combustion shock train (PCST) based on the governing equations for quasi-one-dimensional flow and certain assumptions. Thus the quasi-one-dimensional model of dual-mode scramjet engine that incorporates the changes in wall heat transfer and in the ratio of specific heat is built. Then, the reliability and accuracy of the model are assessed qualitatively and quantitatively by experiment and CFD numerical simulation. There is a high agreement between the theoretical calculations and the results of experimental data and CFD numerical simulation. This work expands the application scope and increases the reliability of quasi-one-dimensional model of dual-mode scramjet engine in RBCC engine. The results shed new light on the preliminary performance assessment and engineering application of dual-mode scramjet engine.
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6

Ji, Zifei, Huiqiang Zhang, and Bing Wang. "Thrust control strategy based on the minimum combustor inlet Mach number to enhance the overall performance of a scramjet engine." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 13 (February 20, 2019): 4810–24. http://dx.doi.org/10.1177/0954410019830816.

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A lower combustor inlet Mach number is desirable in order to design a compact, lightweight combustor and boost the overall performance of the scramjet engine. In this study, a thrust control strategy is proposed for a hydrogen-fueled scramjet taking into account the operating limitations, which is called the minimum combustor inlet Mach number rule since the combustor inlet Mach number is used as the control variable. By scheduling the fuel supply and modifying the intake geometry, the combustor inlet Mach number can be minimized while ensuring a certain thrust output within the operation constraints. In this manner, the scramjet engine can be operated with high specific thrust and low fuel consumption throughout the flight envelope. The thrust control strategy is further applied to a hydrogen-fueled scramjet in the hypersonic flight regime. Because the combustor inlet Mach number varies with flight conditions, the thrust strategy can be applied in practice by monitoring the following aerothermodynamic parameters in different flight regimes instead: (1) combustor outlet Mach number, (2) combustor inlet static temperature, and (3) combustor outlet static temperature. Furthermore, the effects of the thrust output on the division of flight regime are investigated, and the overall performance of the hydrogen-fueled scramjet engine obtained from applying the thrust control strategy is discussed in detail.
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7

Relangi, Naresh, Lakshmi Narayana Phaneendra Peri, Caio Henrique Franco Levi Domingos, Amalia Fossella, Julia Meria Leite Henriques, and Antonella Ingenito. "Design of Supersonic and Hybrid engine based Advanced Rocket (SHAR)." IOP Conference Series: Materials Science and Engineering 1226, no. 1 (February 1, 2022): 012031. http://dx.doi.org/10.1088/1757-899x/1226/1/012031.

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Abstract The paper deals with the design of a two-stage to orbit rocket launcher loaded with a solid rocket booster, scramjet, and hybrid rocket for delivering a 100kg payload in 200 km circular orbit. The possibility of implementing a cavity-based axisymmetric circular combustor in a scramjet is proposed. Computational analysis on various injector locations in a circular combustor and their validation with the test bench results were performed. The utilisation of a hybrid rocket in the final stage of the launcher to deliver the payload is discussed and the performance characteristics of the circular scramjet combustor and the hybrid rocket are shown. The overall mission proposed based on the sustainable and reusable characteristics.
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8

Veeran, Sasha, Apostolos Pesyridis, and Lionel Ganippa. "Ramjet Compression System for a Hypersonic Air Transportation Vehicle Combined Cycle Engine." Energies 11, no. 10 (September 25, 2018): 2558. http://dx.doi.org/10.3390/en11102558.

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This report assesses the performance characteristics of a ramjet compression system in the application of a hypersonic vehicle. The vehicle is required to be self-powered and perform a complete flight profile using a combination of turbojet, ramjet and scramjet propulsion systems. The ramjet has been designed to operate between Mach 2.5 to Mach 5 conditions, allowing for start-up of the scramjet engine. Multiple designs, including varying ramp configurations and turbo-ramjet combinations, were investigated to evaluate their merits and limitations. Challenges arose with attempting to maintain sufficient pressure recoveries and favourable flow characteristics into the ramjet combustor. The results provide an engine inlet design capable of propelling the vehicle between the turbojet and scramjet phase of flight, allowing for the completion of its mission profile. Compromises in the design, however, had to be made in order to allow for optimisation of other propulsion systems including the scramjet nozzle and aerodynamics of the vehicle; it was concluded that these compromises were justified as the vehicle uses the ramjet engine for a minority of the flight profile as it transitions between low supersonic to hypersonic conditions.
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9

Fan, Fa Qing, and Pei Yong Wang. "Investigation of the Non-Equilibrium Flow Phenomena in the Boundary Layer of the Scramjet Engine." Applied Mechanics and Materials 284-287 (January 2013): 795–99. http://dx.doi.org/10.4028/www.scientific.net/amm.284-287.795.

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High-speed and high-temperature are the characteristics of the flow field in scramjet engine; the regular non-slip wall boundary condition requires zero speed at wall; in the same time, the material temperature limit does not allow high wall temperature; therefore the velocity gradient and temperature gradient in the engine boundary layer are huge. If these gradients are too large, the traditional assumption of the local thermal equilibrium in the fluid will fail, the Navier-Stokes equations are no longer valid in the boundary layer. For the first time, the non-equilibrium flow phenomena in Scramjet engine is studied here. Appropriate turbulence model and fine grid are used to analyze the turbulent boundary layer of the Hyshot scramjet engine with three different operating conditions. The result of the CFD simulation shows that the local Knudsen number in the engine boundary layer is greater than the critical value with the operating conditions 40Km/Ma8 and 30Km/Ma8; they are non-equilibrium flow and the Navier-Stokes equations fails. Special treatment of the boundary conditions are needed for these kinds of flow. With the operating condition of 20Km/Ma6, the local thermal equilibrium condition is observed and conventional CFD method is valid.
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10

Zhang, Fan, Huiqiang Zhang, and Bing Wang. "Conceptual study of a dual-rocket-based-combined-cycle powered two-stage-to-orbit launch vehicle." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 5 (May 1, 2017): 944–57. http://dx.doi.org/10.1177/0954410017703148.

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The liquid oxygen/methane staged cycle liquid-rocket engine is one of the most potential rocket engines in the future for its higher performance, higher fuel density and reusable capacity. Two working states of this liquid-rocket engine named as full-load state and half-load state are defined in this paper. Based on this liquid-rocket engine, a dual-rocket-based-combined-cycle propulsion system with liquid oxygen /air/methane as propellants is therefore proposed. The dual-rocket-based-combined-cycle system has then five working modes: the hybrid mode, pure ejector mode, ramjet mode, scramjet mode and pure rocket mode. In hybrid mode, the booster and ejector rockets driven by the full-load liquid-rocket engine work together with the purpose of reducing thrust demand on ejector rocket. In scramjet mode, the fuel-rich burned hot gas generated by the half-load liquid-rocket engine is used as fuel, which is helpful to reduce the technical difficulty of scramjet in hypersonic speed. The five working modes of dual-rocket-based-combined-cycle are highly integrated based on the full- or half-load state of the liquid oxygen/methane staged cycle liquid-rocket engine, and the unified single type fuel of liquid methane is adopted for the whole modes. Then a preliminary design of a horizontal takeoff two-stage-to-orbit launch vehicle is conducted based on the dual-rocket-based-combined-cycle propulsion system. Under an averaged baseline thrust and specific impulse, the launch trajectory to reach a low Earth orbit at 100 km is optimized via the pseudo-spectral method subject to maximizing the payload mass. It is shown that the two-stage-to-orbit vehicle based on the dual-rocket-based-combined-cycle can achieve the payload mass fraction of 0.0469 and 0.0576 for polar mission and equatorial mission, respectively. Conclusively, insights gained in this paper can be usefully applied to a more detailed design of the dual-rocket-based-combined-cycle powered two-stage-to-orbit launch vehicle.
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Дисертації з теми "Scramjet engine"

1

Barone, Dominic L. "Investigation of TDLAS Measurements in a Scramjet Engine." University of Cincinnati / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1277130335.

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2

Zinnecker, Alicia M. "Modeling for Control Design of an Axisymmetric Scramjet Engine Isolator." The Ohio State University, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=osu1354215841.

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3

McGillivray, Nathan T. "Coupling Computational Fluid Dynamics Analysis and Optimization Techniques for Scramjet Engine Design." Wright State University / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=wright1536311445147862.

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4

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 et parvenir à une combustion complète. Les cavités peuvent être utilisées pour augmenter le temps de séjour sans perte excessive de pression totale et sont donc utilisées comme éléments de stabilisation dans les chambres de combustion supersonique. Cette thèse se concentre sur l’étude du mécanisme de stabilisation et des interactions chimie-turbulence dans le cas d’une injection pariétale de combustible dans un écoulement supersonique d’air vicié en amont d’une cavité carrée. Les conditions d’écoulement réactif à grande vitesse correspondantes sont examinées sur la base de simulations numériques d’un modèle de scramjet représentatif d’expériences effectuées précédemment à l’Université du Michigan. Les calculs sont effectués avec le solveur CREAMS, développé pour effectuer la simulation numérique d’écoulements multi-espèces réactifs compressibles sur des architectures massivement parallèles. Le solveur utilise des schémas numériques d’ordre élevé appliqués sur des maillages structurées et la géométrie de la chambre de combustion est modélisée à l’aide d’une méthode de frontières immergées (IBM). Les simulations LES font usage du modèle wall-adapting local eddy (WALE). Deux températures distinctes sont considérées dans l’écoulement entrant d’air vicié pour étudier la stabilisation de la combustion.Une attention particulière est accordée à l’analyse de la topologie et de la structure des écoulements réactifs, les régimes de combustion sont analysés sur la base de diagrammes standards de combustion turbulente
Scramjet engines are high-speed air breathing propulsion systems that do not require rotating elements to compress the air inlet stream. The flow is compressed dynamically through a supersonic intake system integrated in the aircraft’s forebody, reaching the required pressure and temperature for combustion to proceed within the combustor in this kind of engine. The combustion chamber is crossed by a supersonic flow, which limits severely the time available to inject fuel, mix it with oxidizer, ignite the resulting mixture and reach complete combustion. Cavities can be used to increase the residence time without excessive total pressure loss and are therefore used as flame holders in supersonic combustors.This thesis focuses in studying the flame stabilization mechanism and turbulence-chemistry interactions for a jet in a supersonic crossflow (JISCF) of vitiated air with hydrogen injection upstream of a wall-mounted squared cavity. The corresponding reactive high-speed flow conditions are scrutinized on the basis of numerical simulations of a scramjet model representative of experiments previously conducted at the University of Michigan. The computations are performed with the high-performance computational solver CREAMS, developed to perform the numerical simulation of compressible reactive multi-component flows on massively-parallel architectures. The solver makes use of high-order precision numerical schemes applied on structured meshes and the combustion chamber geometry is modeled by using the Immersed Boundary Method (IBM) algorithm. The present set of computations is conducted within the LES framework and the subgrid viscosity is treated with the wall-adapting local eddy (WALE)model. Two distinct temperatures are considered in the inlet vitiated airstream to study combustion stabilization. Special emphasis is placed on the analysis of the reactive flow topology and structure,and the combustion regimes are analyzed on the basis of standard turbulent combustion diagrams
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5

Maddalena, Luca. "Investigations of Injectors for Scramjet Engines." Diss., Virginia Tech, 2007. http://hdl.handle.net/10919/28683.

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An experimental study of an aerodynamic ramp (aeroramp) injector was conducted at Virginia Tech. The aeroramp consisted of an array of two rows with two columns of flush-wall holes that induce vorticity and enhance mixing. For comparison, a single-hole circular injector with the same area angled downstream at 30 degrees was also examined. Test conditions involved sonic injection of helium heated to 313 K, to safely simulate hydrogen into a Mach 4 air cross-stream with average Reynolds number 5.77 e+7 per meter at a jet to freestream momentum flux ratio of 2.1. Sampling probe measurements were utilized to determine the local helium concentration. Pitot and cone-static pressure probes and a diffuser thermocouple probe were employed to document the flow. The main results of this work was that the mixing efficiency value of this aeroramp design which was optimized at Mach 2.4 for hydrocarbon fuel was only slightly higher than that of the single-hole injector at these flow conditions and the mass-averaged total pressure loss parameter showed that the aero-ramp and single-hole injectors had the same overall losses. The natural extension of the investigation was then to look in detail at two major physical phenomena that occurs in a complex injector design such the Aeroramp: the jet-shock interaction and the interaction of the vortical structures produced by the jets injection into a supersonic cross flow. Experimental studies were performed to investigate the effects of impinging shocks on injection of heated helium into a Mach 4 crossflow. It was found that the addition of a shock behind gaseous injection into a Mach 4 crossflow enhances mixing only if the shock is closer to the injection point where the counter-rotating vortex pair (always associated with transverse injection in a crossflow) is not yet formed, and the deposition of baroclinic generated of vorticity is the highest. The final investigation concerned with the interaction of the usual vortex structure produced by jet injection into a supersonic crossflow and an additional axial vortex typical of those that might be produced by the inlet of a scramjet or the forebody of a vehicle to be controlled by jet interaction phenomena. The additional axial vortices were generated by a strut-mounted, diamond cross-section wing mounted upstream of the injection location. The wing was designed to produce a tip vortex of a strength comparable to that of one of the typical counter-rotating vortex pair (CVP) found in the plume of a jet in a crossflow. The profound interaction of supersonic vortices supported by a quantitative description and characterization of the flowfield has been demonstrated.
Ph. D.
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6

Miki, Kenji. "Simulation of magnetohydrodynamics turbulence with application to plasma-assisted supersonic combustion." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/26605.

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Thesis (Ph.D)--Aerospace Engineering, Georgia Institute of Technology, 2009.
Committee Chair: Menon Suresh; Committee Co-Chair: Jagoda Jeff; Committee Member: Ruffin Stephen; Committee Member: Thorsten Stoesser; Committee Member: Walker Mitchell. Part of the SMARTech Electronic Thesis and Dissertation Collection.
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7

Fischer, Christian Max [Verfasser]. "Investigation of the isolator flow of scramjet engines / Christian Max Fischer." Aachen : Hochschulbibliothek der Rheinisch-Westfälischen Technischen Hochschule Aachen, 2014. http://d-nb.info/1059796627/34.

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8

Cocks, Peter. "Large eddy simulation of supersonic combustion with application to scramjet engines." Thesis, University of Cambridge, 2011. https://www.repository.cam.ac.uk/handle/1810/239344.

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This work evaluates the capabilities of the RANS and LES techniques for the simulation of high speed reacting flows. These methods are used to gain further insight into the physics encountered and regimes present in supersonic combustion. The target application of this research is the scramjet engine, a propulsion system of great promise for efficient hypersonic flight. In order to conduct this work a new highly parallelised code, PULSAR, is developed. PULSAR is capable of simulating complex chemistry combustion in highly compressible flows, based on a second order upwind method to provide a monotonic solution in the presence of high gradient physics. Through the simulation of a non-reacting supersonic coaxial helium jet the RANS method is shown to be sensitive to constants involved in the modelling process. The LES technique is more computationally demanding but is shown to be much less sensitive to these model parameters. Nevertheless, LES results are shown to be sensitive to the nature of turbulence at the inflow; however this information can be experimentally obtained. The SCHOLAR test case is used to validate the reacting aspects of PULSAR. Comparing RANS results from laminar chemistry and assumed PDF combustion model simulations, the influence of turbulence-chemistry interactions in supersonic combustion is shown to be small. In the presence of reactions, the RANS results are sensitive to inflow turbulence, due to its influence on mixing. From complex chemistry simulations the combustion behaviour is evaluated to sit between the flamelet and distributed reaction regimes. LES results allow an evaluation of the physics involved, with a pair of coherent vortices identified as the dominant influence on mixing for the oblique wall fuel injection method. It is shown that inflow turbulence has a significant impact on the behaviour of these vortices and hence it is vital for turbulence intensities and length scales to be measured by experimentalists, in order for accurate simulations to be possible.
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Moura, Augusto Fontan. "A computational study of the airflow at the intake region of scramjet engines." Instituto Tecnológico de Aeronáutica, 2014. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=2973.

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This work is part of the research and development, at the Institute for Advanced Studies (IEAv), of the first Brazilian hypersonic vehicle prototype, the 14-X airplane. As this vehicle will be propelled by scramjet (supersonic combustion ramjet) engines, this work presents detailed two-dimensional CFD analyses of the airflow in the intake system of such engines based on the 14-XB scramjet geometry and the expected flight conditions. The main objective is to study the airflow in the intake of the 14-XB at nominal flight condition and also for some off-design flight conditions and geometry using numerical methods and models available in the Fluent code. Off-design values of the vehicle velocity, angle of attack and altitude as well as of the angle of the inlet compression ramp and the number of inlet compression ramps were chosen to show how these changes impact the overall intake airflow. In this study are presented results for the airflow in the entire intake system and of specific flow variables at the engine combustor entrance, as well as calculation results of some intake performance parameters. Both, wall temperature and free stream flow turbulence effects on the intake airflow have also been analyzed. Investigation of viscous flow modeling and of the effects of temperature-dependent air properties has also been performed. Inviscid flow calculations have been performed to serve as a comparison basis for the viscous flow effects and as preliminary information of the airflow. A model validation analysis of the k-kl-? and Transition SST transition models has shown that both models can calculate BL and shock wave interactions (SWBLI) quite well, although, the k-kl-? is better to calculate the separation region whereas the Transition SST is superior to predict the reattachment point. Wall temperature has shown to affect quite significantly SWBLI while viscous flow modeling has shown to have an important impact on the intake airflow with some degradation of the intake system performance.
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10

Najafiyazdi, Alireza. "Theoretical and numerical analysis of supersonic inlet starting by mass spillage." Thesis, McGill University, 2007. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=111524.

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Supersonic inlet starting by mass spillage is studied theoretically and numerically in the present thesis. A quasi-one-dimensional, quasi-steady theory is developed for the analysis of flow inside a perforated inlet. The theory results in closed-form relations applicable to flow starting by the mass spillage technique in supersonic and hypersonic inlets.
The theory involves three parameters to incorporate the multi-dimensional nature of mass spillage through a wall perforation. Mass spillage through an individual slot is studied to determine these parameters; analytical expressions for these parameters are derived for both subsonic and supersonic flow conditions. In the case of mass spillage from supersonic flows, the relations are exact. However, due to the complexity of flow field, the theory is an approximation for subsonic flows. Therefore, a correction factor is introduced which is determined from an empirical relation obtained from numerical simulations.
A methodology is also proposed to determine perforation size and distribution to achieve flow starting for a given inlet at a desired free-stream Mach number. The problem of shock stability inside a perforated inlet designed with the proposed method is also discussed.
The method is demonstrated for some test cases. Time-realistic CFD simulations and experimental results in the literature confirm the accuracy of the theory and the reliability of the proposed design methodology.
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Книги з теми "Scramjet engine"

1

The scramjet engine: Processes and characteristics. Cambridge: Cambridge University Press, 2009.

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2

Burkardt, Leo A. RAMSCRAM: A flexible ramjet/scramjet engine simulation program. [Washington, DC]: National Aeronautics and Space Administration, 1990.

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3

Center, Langley Research, ed. Internal aerodynamics of a generic three-dimensional scramjet inlet at Mach 10. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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4

Center, Langley Research, ed. Mach 10 experimental database of a three-dimensional scramjet inlet flow field. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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5

Holland, Scott D. Mach 10 experimental database of a three-dimensional scramjet inlet flow field. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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6

Center, Langley Research, ed. Wind-tunnel blockage and actuation systems test of a two-dimensional scramjet inlet unstart model at Mach 6. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

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7

Center, Langley Research, ed. Wind-tunnel blockage and actuation systems test of a two-dimensional scramjet inlet unstart model at Mach 6. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

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8

Center, Langley Research, ed. Wind-tunnel blockage and actuation systems test of a two-dimensional scramjet inlet unstart model at Mach 6. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

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9

T, Curran E., and Murthy S. N. B, eds. Scramjet propulsion. Reston, Va: American Institute of Aeronautics and Astronautics, 2000.

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10

Schetz, Joseph A. Studies in scramjet flowfields. [S.l.]: American Institute of Aeronautics and Astronautics, 1987.

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Частини книг з теми "Scramjet engine"

1

Babu, V. "Ramjet and Scramjet Engine." In Fundamentals of Propulsion, 135–53. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-79945-8_8.

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2

Jose, Riyan Cyriac, Rhitik Raj, Yogesh Dewang, and Vipin Sharma. "A Review on Scramjet Engine." In Lecture Notes in Mechanical Engineering, 539–48. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-0159-0_48.

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3

Kumar, Ajay. "Numerical Simulation of Scramjet Engine Flowfield." In Hypersonic Flows for Reentry Problems, 89–110. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-77922-0_15.

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4

Arjun, P., and S. R. Nagaraja. "Unstart Phenomenon in a Scramjet Engine Isolator." In Recent Advances in Thermofluids and Manufacturing Engineering, 195–204. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-4388-1_18.

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5

Masuya, Goro, Nobuo Chinzei, and Yoichiro Miki. "Scramjet Engine Tests at Mach 4 and 6." In Fluid Mechanics and Its Applications, 147–62. Dordrecht: Springer Netherlands, 1997. http://dx.doi.org/10.1007/978-94-011-5432-1_12.

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6

Rowan, S., T. Komuro, K. Sato, and K. Itoh. "Combustion performance of a scramjet engine with inlet injection." In Shock Waves, 553–58. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-85168-4_88.

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7

Du, Jinfeng, Chun Guan, Yuchun Chen, Haomin Li, and Zhihua Wang. "Analysis of Overall Performance of Multi-stage Combustor Scramjet Engine." In Lecture Notes in Electrical Engineering, 1835–46. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_147.

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8

Vijayakumar, G. "Thermal Design Methodology for Regenerative Fuel-Cooled Scramjet Engine Walls." In Advances in Applied Mechanical Engineering, 269–77. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-1201-8_31.

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9

Verma, Kumari Ambe, K. M. Pandey, and K. K. Sharma. "Study of Fuel Injection Systems in Scramjet Engine—A Review." In Lecture Notes in Mechanical Engineering, 931–40. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-15-7711-6_92.

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Naveen, K., Mukesh Kapoor, M. S. Prasad, and S. Arunvinthan. "Design and Analysis of a Novel Cloverleaf Combustor for Scramjet Engine." In Lecture Notes in Mechanical Engineering, 51–63. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-6469-3_5.

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Тези доповідей конференцій з теми "Scramjet engine"

1

Burkardt, Leo A., and Leo C. Franciscus. "RAMSCRAM: A Flexible RAMJET/SCRAMJET Engine Simulation Program." In ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1990. http://dx.doi.org/10.1115/90-gt-323.

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With the resurgence of interest in high supersonic and hypersonic flight there is a need to simulate airbreathing engines which may be used in this flight regime. To meet this requirement the RAMSCRAM code was developed. The code calculates one-dimensional flow properties at each component interface and the overall performance of the engine. It uses equilibrium thermodynamics which accounts for dissociation and allows for any fuel or combination of fuels. The program can simulate ramjet, scramjet, rocket, and ducted rocket engines.
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2

Huang, Wei, Zhen-guo Wang, Shi-bin Luo, Jun Liu, Zhi-xun Xia, Jing Lei, Liang Jin, et al. "Overview of Fuel Injection Techniques for Scramjet Engines." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-45064.

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As one of the most promising hypersonic propulsion systems for hypersonic vehicles, the scramjet engine has drawn an ever increasing attention of researchers worldwide. At present, one of the most important issues to be dealt with is how to improve the fuel penetration and mixing efficiency and make the flame stable in supersonic flows. Further, how to reduce the structural weight of the engines is an urgent issue that needs to be considered. The ongoing research efforts on fuel injection techniques in the scramjet engine are described, mainly the cavity flame holder, the backward facing step, the strut injection and the cantilevered ramp injection, and the flow field characteristics and research efforts related to these fuel injection techniques are summarized and compared. Finally, a promising fuel injection technique is discussed, namely a combination of different injection techniques, and the combination of the cantilevered ramp injector and the cavity flame holder is proposed. This is because it can not only stabilize the flame, but also shorten the length of the combustor, thus lighten the weight of the scramjet engines.
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3

He, Yongpan, Yuchun Chen, Dingxin Liu, Jie Liu, Mourong Lai, and Xiao Liang. "Research on Solid Rocket/Scramjet Combined Engine." In 21st AIAA International Space Planes and Hypersonics Technologies Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-2390.

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4

Kanda, Takeshi. "Simulation of an airframe-integrated scramjet engine." In 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-3427.

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5

Flock, Andreas K., Johannes C. Riehmer, and Ali Guelhan. "Axisymmetric SCRamjet Engine Design and Performance Analysis." In 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-3628.

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6

Kanda, Takeshi, Yoshio Wakamatsu, Fumiei Ono, Kenji Kudo, Atsuo Murakami, and Muneo Izumikawa. "Mach 8 testing of scramjet engine models." In 37th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-617.

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7

Sato, Shigeru, Masaaki Fukui, Takahiro Watanabe, Masaharu Takahashi, and Toshihiko Munakata. "Trial for Improvement in Scramjet Engine Performance." In 2018 AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-0889.

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8

Risha, D. "Simulated engine and component performance of a pylon fueled scramjet engine." In 38th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-618.

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9

Tomioka, Sadatake, Shuuichi Ueda, Kohichiro Tani, and Takeshi Kanda. "Scramjet Engine Tests at Ramjet Engine Test Facility in JAXA-KSPC." In 45th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-1040.

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10

Chinzei, Nobuo. "Progress in scramjet engine tests at NAL-KRC." In 10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-1883.

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Звіти організацій з теми "Scramjet engine"

1

McRae, D. S., and Jack R. Edwards. Dynamic Computational Analyses of Complete Scramjet Engine Modules. Fort Belvoir, VA: Defense Technical Information Center, September 2001. http://dx.doi.org/10.21236/ada399718.

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2

Yu, Shaeng-Tao J., Chang-Kee Kim, and Zeng-Chan Zhang. Simulation of High-Speed Cavity Flows in a Scramjet Engine by the Space-Time CESE Method. Fort Belvoir, VA: Defense Technical Information Center, September 2005. http://dx.doi.org/10.21236/ada439707.

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3

Noone, Emily, and Lydia Harriss. Hypersonic missiles. Parliamentary Office of Science and Technology, June 2023. http://dx.doi.org/10.58248/pn696.

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Анотація:
This POSTnote looks at hypersonic missile technologies, efforts to develop them, potential applications, and the possible challenges they may present for missile defence and global stability. Key Points: • Hypersonic missiles combine speeds of over five times the speed of sound with significant manoeuvrability during flight. • Their manoeuvrability enables them to change trajectory during flight, making their flight-path and target difficult to predict. • They fly at lower altitudes than ballistic missiles, which means that they may be harder to track at long distances with some surface-based sensors, such as certain radar. • There are two main types of hypersonic missile: hypersonic glide vehicles (HGVs) and hypersonic cruise missiles (HCMs). • HGVs are mounted onto rocket boosters for launch and may be accelerated to speeds of Mach 20 or more. The glider then separates from the booster and flies unpowered in the Earth’s upper atmosphere at altitudes of 30-80 km, before diving towards the target. • HCMs typically have a ramjet or scramjet engine that enables them to reach hypersonic speeds at altitudes of 20-40 km. • China and Russia have reportedly deployed hypersonic missiles that could deliver conventional or nuclear weapons. The US is testing multiple hypersonic technologies. • The AUKUS agreement between the UK, US and Australia includes developing hyper-sonic and counter-hypersonic technologies. • Developing hypersonic missiles requires significant research and development challenges to be overcome, contributing to their high development and manufacturing costs. • The speed, manoeuvrability and altitude of hypersonic missiles may challenge existing missile defences, although their uses and effectiveness are still being assessed. • Defence analysts disagree about the potential implications of hypersonic missiles for global peace and stability. Some suggest they could increase the risk of conflict escalation, while others say that they will not alter the strategic balance between nuclear powers. • Arms control, export controls and other measures may help limit potential harm to peace and stability, but these approaches face challenges.
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