Relevant bibliographies by topics / Scramjet

Academic literature on the topic 'Scramjet'

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Published: 4 June 2021
Last updated: 6 September 2023

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Journal articles on the topic "Scramjet"

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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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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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Meng, Yu, Wenming Sun, Hongbin Gu, Fang Chen, and Ruixu Zhou. "Supersonic Combustion Mode Analysis of a Cavity Based Scramjet." Aerospace 9, no. 12 (December 15, 2022): 826. http://dx.doi.org/10.3390/aerospace9120826.

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Since flame stability is the key to the performance of scramjets, scramjet combustion mode and instability characteristics were investigated by using the POD method based on a cavity-stabilized scramjet. Experiments were developed on a directly connected scramjet model that had an inlet flow of Mach 2.5 with a cavity stabilizer. CH* chemiluminescence, schlieren, and a wall static pressure sensor were employed to observe flow and combustion behavior. Three typical combustion modes were classified by distinguishing averaged CH* chemiluminescence images of three ethylene fuel jet equivalence ratios. The formation reason was explained using schlieren images and pressure characteristics. POD modes (PDMs) were determined using the proper orthogonal decomposition (POD) of sequential flame CH* chemiluminescence images. The PSD (power spectral density) of the PDM spectra showed large peaks in a frequency range of 100–600 Hz for three typical stabilized combustion modes. The results provide oscillation characteristics of three scramjet combustion modes.
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Paull, A., R. J. Stalker, and D. J. Mee. "Scramjet thrust measurement in a shock tunnel." Aeronautical Journal 99, no. 984 (April 1995): 161–63. http://dx.doi.org/10.1017/s0001924000027147.

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This note reports tests in a shock tunnel in which a fully integrated scramjet configuration produced net thrust. The experiments not only showed that impulse facilities can be used for assessing thrust performance, but also were a demonstration of the application of a new technique(1) to the measurement of thrust on scramjet configurations in shock tunnels. These two developments are of significance because scramjets are expected to operate at speeds well in excess of 2 km/s, and shock tunnels offer a means of generating high Mach number flows at such speeds.
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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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Stalker, R. J., N. K. Truong, R. G. Morgan, and A. Paull. "Effects of hydrogen–air non–equilibrium chemistry on the performance of a model scramjet thrust nozzle." Aeronautical Journal 108, no. 1089 (November 2004): 575–84. http://dx.doi.org/10.1017/s0001924000000403.

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AbstractTwo aspects of hydrogen-air non-equilibrium chemistry related to scramjets are nozzle freezing and a process called ‘kinetic afterburning’ which involves continuation of combustion after expansion in the nozzle. These effects were investigated numerically and experimentally with a model scramjet combustion chamber and thrust nozzle combination. The overall model length was 0·5m, while precombustion Mach numbers of 3·1±0·3 and precombustion temperatures ranging from 740K to 1,400K were involved. Nozzle freezing was investigated at precombustion pressures of 190kPa and higher, and it was found that the nozzle thrusts were within 6% of values obtained from finite rate numerical calculations, which were within 7% of equilibrium calculations. When precombustion pressures of 70kPa or less were used, kinetic afterburning was found to be partly responsible for thrust production, in both the numerical calculations and the experiments. Kinetic afterburning offers a means of extending the operating Mach number range of a fixed geometry scramjet.
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CHINZEI, Nobuo, and Goro MASUYA. "Scramjet Engines." Journal of the Society of Mechanical Engineers 94, no. 866 (1991): 75–80. http://dx.doi.org/10.1299/jsmemag.94.866_75.

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Ouyang, Hao, Weidong Liu, and Mingbo Sun. "Investigations on the Influence of the In-Stream Pylon and Strut on the Performance of a Scramjet Combustor." Scientific World Journal 2014 (2014): 1–10. http://dx.doi.org/10.1155/2014/309387.

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The influence of the in-stream pylon and strut on the performance of scramjet combustor was experimentally and numerically investigated. The experiments were conducted with a direct-connect supersonic model combustor equipped with multiple cavities. The entrance parameter of combustor corresponds to scramjet flight Mach number 4.0 with a total temperature of 947 K. The research results show that, compared with the scramjet combustor without pylon and strut, the wall pressure and the thrust of the scramjet increase due to the improvement of mixing and combustion effect due to the pylon and strut. The total pressure loss caused by the strut is considerable whereas pylon influence is slight.
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Yang, Pengnian, Zhixun Xia, Likun Ma, Binbin Chen, Yunchao Feng, Chaolong Li, and Libei Zhao. "Direct-Connect Test of Solid Scramjet with Symmetrical Structure." Energies 14, no. 17 (September 6, 2021): 5589. http://dx.doi.org/10.3390/en14175589.

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The solid scramjet has become one of the most promising engine types. In this paper, we report the first direct-connect test of a solid scramjet with symmetrical structure, carried out using boron-based fuel-rich solid propellant as fuel. During the test, which simulated a flight environment at Mach 5.6 and 25 km, the performance of the solid scramjet was obtained by measuring the pressure, thrust, and mass flow. The results show that, due to the change in the combustion area of the propellant and the deposition of the throat in the gas generator during the test, the equivalence ratio gradually increased from 0.54 to 0.63. In a solid scramjet, it is possible to obtain a symmetrical distribution of the flow field within the combustor. Moreover, in a multi-cavity combustor, the combustion state expands from the cavity to the center of the flow channel. The performance of the solid scramjet increased during the test, reaching a combustion efficiency of about 42%, a total pressure recovery coefficient of 0.35, and a thrust gain specific impulse of about 418 s. The solid scramjet with symmetrical structure is feasible. The cavity configuration adopted in this paper can reduce the ignition delay time of fuel-rich gas and improve the combustion efficiency of gas-phase combustible components. The shock trains in the isolator are conducive to the recovery of the total pressure. The performance of the solid scramjet is limited by the low combustion efficiency of the particles.
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Fureby, Christer, Guillaume Sahut, Alessandro Ercole, and Thommie Nilsson. "Large Eddy Simulation of Combustion for High-Speed Airbreathing Engines." Aerospace 9, no. 12 (December 1, 2022): 785. http://dx.doi.org/10.3390/aerospace9120785.

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Large Eddy Simulation (LES) has rapidly developed into a powerful computational methodology for fluid dynamic studies, between Reynolds-Averaged Navier–Stokes (RANS) and Direct Numerical Simulation (DNS) in both accuracy and cost. High-speed combustion applications, such as ramjets, scramjets, dual-mode ramjets, and rotating detonation engines, are promising propulsion systems, but also challenging to analyze and develop. In this paper, the building blocks needed to perform LES of high-speed combustion are reviewed. Modelling of the unresolved, subgrid terms in the filtered LES equations is highlighted. The main families of combustion models are presented, focusing on finite-rate chemistry models. The density-based finite volume method and the reaction mechanisms commonly employed in LES of high-speed H2-air combustion are briefly reviewed. Three high-speed combustor applications are presented: an experiment of supersonic flame stabilization behind a bluff body, a direct connect facility experiment as a transition case from ramjet to scramjet operation mode, and the STRATOFLY MR3 Small-Scale Flight Experiment. Several combinations of turbulence and combustion models are compared. Comparisons with experiments are also provided when available. Overall, the results show good agreement with experimental data (e.g., shock train, mixing, wall heat flux, transition from ramjet to scramjet operation mode).
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Dissertations / Theses on the topic "Scramjet"

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Matthews, Alexander J. "Scramjet intakes." Thesis, University of Oxford, 2003. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.400217.

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Odam, Judy. "Scramjet experiments using radical farming /." [St. Lucia, Qld.], 2004. http://adt.library.uq.edu.au/public/adt-QU20041206.101729/index.html.

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Schütte, Gerrit. "Probabilistische Untersuchungen zu Scramjet-Antriebssystemen." Aachen Shaker, 2009. http://d-nb.info/1000474291/04.

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McGuire, Jeffrey Robert Aerospace Civil &amp Mechanical Engineering Australian Defence Force Academy UNSW. "Ignition enhancement for scramjet combustion." Awarded by:University of New South Wales - Australian Defence Force Academy. School of Aerospace, Civil and Mechanical Engineering, 2007. http://handle.unsw.edu.au/1959.4/38748.

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The process of shock-induced ignition has been investigated both computa- tionally and experimentally, with particular emphasis on the concept of radical farming. The first component of the investigation contained Computational Fluid Dynamic (CFD) calculations of an ignition delay study, a 2D pre-mixed flow over flat plate at a constant angle to the freestream, and through a generic 2D scramjet model. The focal point of the investigation however examined the complex 3D flow through a generic scramjet model. Five experimental test conditions were ex- amined over flow enthalpies from 3.4 MJ/kg to 6.4 MJ/kg. All test conditions simulated flight at 21000 metres ([symbol=almost equal to] 70000 ft), while the equivalent flight Mach number varied from approximately 8.5 at the lowest enthalpy, to approximately Mach 12 at the highest enthalpy condition. The presence of H2 fuel injected in the intake caused a separated region to form on the lower surface of the model at the entrance to the combustor. A fraction of the total mass of fuel was entrained in this separated region, providing long residence times, hence increased time for the chemical reactions that lead to ignition to occur. In addition, extremely high temperatures were found to exist between each fuel jet. Both fuel and air are present in these regions, therefore the chance of ignition in these regions is high. Streamlines passing through the recirculation zone ignited within this zone, while streamlines passing between the fuel jets ignited soon after entry into the combustor. The first instance of a pressure rise from combustion was observed on the centreline of the model where the reflected bow shock around the fuel jets crossed the centreline of the combus- tor. Upstream of this location the static pressure of the flow was too low for the chemical reactions that release heat to occur. The comparison between the experimental and computational results was lim- ited due to inaccuracies in modelling the thermal state of the gas in the CFD calculations. The gas was modelled as being in a state of thermal equilibrium at all times, which incorrectly models the freestream flow from the nozzle of the shock tunnel, and also the flow downstream of oblique shock wave within the scramjet model. As a result combustion occurs sooner in the CFD calculations than in the experimental result.
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Biasca, Rodger Joseph. "Chemical kinetics of SCRAMJET propulsion." Thesis, Massachusetts Institute of Technology, 1988. http://hdl.handle.net/1721.1/35949.

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Gardner, Anthony D. "HyShot scramjet testing in the HEG /." Köln : DLR, Bibliotheks- und Informationswesen, 2007. http://bvbr.bib-bvb.de:8991/F?func=service&doc_library=BVB01&doc_number=016271138&line_number=0001&func_code=DB_RECORDS&service_type=MEDIA.

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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.
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Ingenito, Antonella. "Modellistica della combustione in regime supersonico." Doctoral thesis, La Sapienza, 2006. http://hdl.handle.net/11573/917117.

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Prebola, John L. Jr. "Performance of a Plasma Torch with Hydrocarbon Feedstocks for Use in Scramjet Combustion." Thesis, Virginia Tech, 1998. http://hdl.handle.net/10919/36941.

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Research was conducted at Virginia Tech on a high-pressure uncooled plasma torch to study torch operational characteristics with hydrocarbon feedstocks and to determine the feasibility of using the torch as an igniter in scramjet applications. Operational characteristics studied included electrical properties, such as arc stability, voltage-current characteristics and start/re-start capabilities, and mechanical properties, such as coking, electrode erosion and transient to steady-state torch body temperature trends. Possible use of the plasma torch as an igniter in high-speed combustion environments was investigated through the use of emission spectroscopy and a NASA chemical kinetics code. All feedstocks tested; argon, methane, ethylene and propylene, were able to start. The voltage data indicated that there were two preferred operating modes, which were well defined for methane. For all gases, a higher current setting, on the order of 40 A, led to more stable torch operation. A low intensity, high frequency current applied to the torch, along with the primary DC current, resulted in virtual elimination of soot deposits on the anodes. Electrode erosion was found to multiply each time the complexity of the hydrocarbon was increased. Audio and high-speed visual analysis led to identification of 180 Hz plasma formation cycle, related to the three-phase power supply. The spectroscopic analysis aided in the identification of combustion enhancing radicals being produced by the torch, and results of the chemical kinetics analysis verified combustion enhancement and radical production through the use of a basic plasma model. Overall, the results of this study indicate that the plasma torch is a promising source for scramjet ignition, and further study is warranted.
Master of Science
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Rowan, Scott A. "Viscous drag reduction in a scramjet combustor /." St. Lucia, Qld, 2003. http://www.library.uq.edu.au/pdfserve.php?image=thesisabs/absthe17438.pdf.

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Books on the topic "Scramjet"

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

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United States. National Aeronautics and Space Administration., ed. A first scramjet study. [Washington, DC: National Aeronautics and Space Administration, 1989.

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J, Aslan, and Universities Space Research Association, eds. OVRhyp: Scramjet test aircraft. Houston, Tex: Universities Space Research Association, 1990.

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

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, ed. Heat pipe cooling for scramjet engines. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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

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J, Bakos Robert, and Langley Research Center, eds. Shock tunnel studies of scramjet phenomena. St. Lucia, Qld: University of Queensland, 1991.

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G, Morgan R., and Langley Research Center, eds. Shock tunnel studies of scramjet phenomena. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1988.

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Ishiguro, Tomiko. Numerical calculation of scramjet inlet flow. Tokyo, Japan: National Aerospace Laboratory, 1992.

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R, Casey, and Langley Research Center, eds. Shock tunnel studies of scramjet phenomena. St. Lucia, Qld: University of Queensland, 1990.

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Book chapters on the topic "Scramjet"

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Bitterlich, Walter, and Ulrich Lohmann. "Scramjet." In Gasturbinenanlagen, 395–97. Wiesbaden: Springer Fachmedien Wiesbaden, 2018. http://dx.doi.org/10.1007/978-3-658-15067-9_28.

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Shapiro, Richard A. "Scramjet Inlets." In Adaptive Finite Element Solution Algorithm for the Euler Equations, 120–37. Wiesbaden: Vieweg+Teubner Verlag, 1991. http://dx.doi.org/10.1007/978-3-322-87879-3_8.

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Shapiro, Richard A. "Scramjet Geometry Definition." In Adaptive Finite Element Solution Algorithm for the Euler Equations, 152–53. Wiesbaden: Vieweg+Teubner Verlag, 1991. http://dx.doi.org/10.1007/978-3-322-87879-3_11.

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Morgan, R. G., and F. Zander. "Radiatively cooled scramjet combustor." In Shock Waves, 1135–40. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-85181-3_55.

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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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El-Sayed, Ahmed F. "Pulsejet, Ramjet, and Scramjet Engines." In Fundamentals of Aircraft and Rocket Propulsion, 315–401. London: Springer London, 2016. http://dx.doi.org/10.1007/978-1-4471-6796-9_5.

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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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Li, J. P., W. Y. Song, and Y. Xing. "Research on Nozzle Performance in Scramjet." In New Trends in Fluid Mechanics Research, 287. Berlin, Heidelberg: Springer Berlin Heidelberg, 2007. http://dx.doi.org/10.1007/978-3-540-75995-9_89.

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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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Swithenbank, J., B. C. R. Ewan, S. B. Chin, L. Shao, and Y. Wu. "Mixing Power Concepts in Scramjet Combustor Design." In ICASE/NASA LaRC Series, 531–84. New York, NY: Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2884-4_26.

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Conference papers on the topic "Scramjet"

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STULL, F. "Scramjet propulsion." In National Aerospace Plane Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-5012.

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Druss, Ryan I., Marc D. Polanka, Timothy Ombrello, and Frederick Schauer. "Scramjet Operability and RDE Design for RDE Piloted Scramjet." In AIAA Scitech 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-0199.

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Ryken, Marv, and R. Davis. "Scramjet Antenna Development." In 24th AIAA Aerodynamic Measurement Technology and Ground Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-2741.

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Zander, Fabian, and Richard Morgan. "Composite Scramjet Combustor." In 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-7354.

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Idris, A. C., M. R. Saad, and K. Kontis. "Microvortex generator for scramjet inlet application." In Progress in Propulsion Physics – Volume 11. Les Ulis, France: EDP Sciences, 2019. http://dx.doi.org/10.1051/eucass/201911747.

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Global measurement approach in characterizing a generic scramjet inlet has enabled the investigation of various flow phenomena typically occurred on an inlet to be investigated further. This paper examines the effectiveness of microvortex generator (MVG) array in suppressing boundary layer separations on such an inlet. Global measurement of pressure and temperature were employed to visualize vortex pairs emanating from the MVG. The global pressure map showed the benefit of lower reattachment peak pressure that usually accompanies the large separation bubble at a scramjet inlet throat.
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Ingenito, A., S. Gulli, and C. Bruno. "Sizing of scramjet vehicles." In Progress in Propulsion Physics. Les Ulis, France: EDP Sciences, 2011. http://dx.doi.org/10.1051/eucass/201102487.

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SCHETZ, J., and F. BILLIG. "Studies of scramjet flowfields." In 23rd Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2161.

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Chen, Yen-Sen, Y. Y. Lian, Bill Wu, and J. S. Wu. "Scramjet Combustor Computational Modeling." In 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-5386.

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Boyce, R., and A. Paull. "Scramjet intake and exhaust CFD studies for the HyShot scramjet flight experiment." 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/10.2514/6.2001-1891.

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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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Reports on the topic "Scramjet"

1

O'Byrne, Sean, S. Wittig, J. Kurtz, Y. Krishna, C. Rodriguez, M. Aizengendler, and J. Davies. Diode Laser Sensor for Scramjet Inlets. Fort Belvoir, VA: Defense Technical Information Center, June 2011. http://dx.doi.org/10.21236/ada544361.

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2

Hagenmaier, Mark A., John Boles, and Ryan T. Milligan. Scramjet Research with Flight-Like Inflow Conditions. Fort Belvoir, VA: Defense Technical Information Center, July 2013. http://dx.doi.org/10.21236/ada589252.

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Chambers Jr, Harold F. Applying MHD Results to a Scramjet Vehicle. Fort Belvoir, VA: Defense Technical Information Center, February 2007. http://dx.doi.org/10.21236/ada463441.

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4

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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5

Schneider, Steven P., and Helen L. Reed. Mechanisms of Hypersonic Transition on a Generic Scramjet Forebody. Fort Belvoir, VA: Defense Technical Information Center, February 2003. http://dx.doi.org/10.21236/ada413763.

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6

Hagenmaier, Mark A., Dean R. Eklund, and Ryan T. Milligan. Improved Simulation of Inflow Distortion for Direct-Connect Scramjet Studies. Fort Belvoir, VA: Defense Technical Information Center, April 2011. http://dx.doi.org/10.21236/ada543745.

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7

Hallion, Richard P., John Becker, John Vitalli, and James Young. The Hypersonic Revolution. Volume 2. From Scramjet to the National Aero-Space Plane. Fort Belvoir, VA: Defense Technical Information Center, August 1995. http://dx.doi.org/10.21236/ada302634.

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8

Brown, Michael S., Skip Williams, Chadwick D. Lindstrom, and Dominic L. Barone. Progress in Applying Tunable Diode Laser Absorption Spectroscopy to Scramjet Isolators and Combustors. Fort Belvoir, VA: Defense Technical Information Center, May 2010. http://dx.doi.org/10.21236/ada522512.

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9

Chen, Ping-Chih, Ryan Starkey, Kai-Ti Chang, and Ayan Sengupta. Integrated Aero-Servo-Thermo-Propulso-Elasticity (ASTPE) for Hypersonic Scramjet Vehicle Design/Analysis. Fort Belvoir, VA: Defense Technical Information Center, December 2009. http://dx.doi.org/10.21236/ada590178.

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10

Boles, John, and Ryan Milligan. Technology for Sustained Supersonic Combustion Task Order 0006: Scramjet Research with Flight-Like Inflow Conditions. Fort Belvoir, VA: Defense Technical Information Center, January 2013. http://dx.doi.org/10.21236/ada586382.

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