Log in

Relevant bibliographies by topics / Scramjet engines / Journal articles

To see the other types of publications on this topic, follow the link: Scramjet engines.

Journal articles on the topic 'Scramjet engines'

Author: Grafiati

Published: 4 June 2021

Last updated: 6 September 2023

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the top 50 journal articles for your research on the topic 'Scramjet engines.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Browse journal articles on a wide variety of disciplines and organise your bibliography correctly.

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

2

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.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

4

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

5

Tsujikawa, Y., and M. Nagaoka. "Determination of Cycle Configuration of Gas Turbines and Aircraft Engines by an Optimization Procedure." Journal of Engineering for Gas Turbines and Power 113, no. 1 (January 1, 1991): 100–105. http://dx.doi.org/10.1115/1.2906515.

Full text

Abstract:

This paper is devoted to the analyses and optimization of simple and sophisticated cycles, particularly for various gas turbine engines and aero-engines (including the scramjet engine) to achieve maximum performance. The optimization of such criteria as thermal efficiency, specific output, and total performance for gas turbine engines, and overall efficiency, nondimensional thrust, and specific impulse for aero-engines has been performed by the optimization procedure with the multiplier method. Comparison of results with analytical solutions establishes the validity of the optimization procedure.

APA, Harvard, Vancouver, ISO, and other styles

6

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.

Full text

Abstract:

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).

APA, Harvard, Vancouver, ISO, and other styles

7

Curran, Edward T. "Scramjet Engines: The First Forty Years." Journal of Propulsion and Power 17, no. 6 (November 2001): 1138–48. http://dx.doi.org/10.2514/2.5875.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

Atashi-Abkenar, M. A. "Study on the Effect of Two Uncertainty Parameters on Scramjet Engine Using Monte Carlo Simulation." International Journal of Mathematical Models and Methods in Applied Sciences 16 (May 13, 2022): 89–94. http://dx.doi.org/10.46300/9101.2022.16.16.

Full text

Abstract:

Today, aerospace engines are developing rapidly, these engines are divided into two groups of gas turbines and without gas turbines. In this thesis, the thermodynamic performance of the scramjet engine is examined. This study is carried out with consideration of uncertainty parameters. Two parameters of the combustion chamber efficiency and heating value of fuel are considered as uncertainty parameters. Using Monte Carlo numerical simulation method, the functional curves of the scramjet engine were investigated, and Analysis is done. According to the use of uncertainty parameters, first, a brief explanation of the uncertainty illustrates according to calculate using their functions and the Monte Carlo method. Also, the uncertain effects on the functional charts are analyzed considering the variable taking into account each of the uncertainty parameters. According to the obtained results, it was determined that the uncertain effect of the combustion chamber is negligible compared to the heating value of the fuel, the number of different points of 100,200 and 300 is similar to each other, and according to the extracted functional charts With regard to the uncertainties, it was observed that the least compression efficiency and special fuel consumption would have the greatest effect from the uncertainties.

APA, Harvard, Vancouver, ISO, and other styles

9

Taha, A. A., S. N. Tiwari, and T. O. Mohieldin. "Combustion Characteristics of Ethylene in Scramjet Engines." Journal of Propulsion and Power 18, no. 3 (May 2002): 716–18. http://dx.doi.org/10.2514/2.5989.

Full text

APA, Harvard, Vancouver, ISO, and other styles

10

TOMIOKA, Sadatake, Tetsuo HIRAIWA, Tomoyuki KISHIDA, and Hiroyuki YAMASAKI. "Evaluation of Vitiation Effects in Scramjet Engines." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 7, ists26 (2009): Pa_47—Pa_52. http://dx.doi.org/10.2322/tstj.7.pa_47.

Full text

APA, Harvard, Vancouver, ISO, and other styles

11

Mitani, Tohru, Nobuo Chinzei, and Takeshi Kanda. "Reaction and Mixing-Controlled Combustion in Scramjet Engines." Journal of Propulsion and Power 17, no. 2 (March 2001): 308–14. http://dx.doi.org/10.2514/2.5743.

Full text

APA, Harvard, Vancouver, ISO, and other styles

12

Seiner, John M., S. M. Dash, and D. C. Kenzakowski. "Historical Survey on Enhanced Mixing in Scramjet Engines." Journal of Propulsion and Power 17, no. 6 (November 2001): 1273–86. http://dx.doi.org/10.2514/2.5876.

Full text

APA, Harvard, Vancouver, ISO, and other styles

13

Choubey, Gautam, Yuvarajan D, Wei Huang, Li Yan, Houman Babazadeh, and K. M. Pandey. "Hydrogen fuel in scramjet engines - A brief review." International Journal of Hydrogen Energy 45, no. 33 (June 2020): 16799–815. http://dx.doi.org/10.1016/j.ijhydene.2020.04.086.

Full text

APA, Harvard, Vancouver, ISO, and other styles

14

Liu, Xiaonan, and Yufei Ma. "Tunable Diode Laser Absorption Spectroscopy Based Temperature Measurement with a Single Diode Laser Near 1.4 μm." Sensors 22, no. 16 (August 15, 2022): 6095. http://dx.doi.org/10.3390/s22166095.

Full text

Abstract:

The rapidly changing and wide dynamic range of combustion temperature in scramjet engines presents a major challenge to existing test techniques. Tunable diode laser absorption spectroscopy (TDLAS) based temperature measurement has the advantages of high sensitivity, fast response, and compact structure. In this invited paper, a temperature measurement method based on the TDLAS technique with a single diode laser was demonstrated. A continuous-wave (CW), distributed feedback (DFB) diode laser with an emission wavelength near 1.4 μm was used for temperature measurement, which could cover two water vapor (H2O) absorption lines located at 7153.749 cm−1 and 7154.354 cm−1 simultaneously. The output wavelength of the diode laser was calibrated according to the two absorption peaks in the time domain. Using this strategy, the TDLAS system has the advantageous of immunization to laser wavelength shift, simple system structure, reduced cost, and increased system robustness. The line intensity of the two target absorption lines under room temperature was about one-thousandth of that under high temperature, which avoided the measuring error caused by H2O in the environment. The system was tested on a McKenna flat flame burner and a scramjet model engine, respectively. It was found that, compared to the results measured by CARS technique and theoretical calculation, this TDLAS system had less than 4% temperature error when the McKenna flat flame burner was used. When a scramjet model engine was adopted, the measured results showed that such TDLAS system had an excellent dynamic range and fast response. The TDLAS system reported here could be used in real engine in the future.

APA, Harvard, Vancouver, ISO, and other styles

15

Jiang, Yuguang, Yu Feng, Silong Zhang, Jiang Qin, and Wen Bao. "Numerical heat transfer analysis of transcritical hydrocarbon fuel flow in a tube partially filled with porous media." Open Physics 14, no. 1 (January 1, 2016): 659–67. http://dx.doi.org/10.1515/phys-2016-0073.

Full text

Abstract:

AbstractHydrocarbon fuel has been widely used in air-breathing scramjets and liquid rocket engines as coolant and propellant. However, possible heat transfer deterioration and threats from local high heat flux area in scramjet make heat transfer enhancement essential. In this work, 2-D steady numerical simulation was carried out to study different schemes of heat transfer enhancement based on a partially filled porous media in a tube. Both boundary and central layouts were analyzed and effects of gradient porous media were also compared. The results show that heat transfer in the transcritical area is enhanced at least 3 times with the current configuration compared to the clear tube. Besides, the proper use of gradient porous media also enhances the heat transfer compared to homogenous porous media, which could help to avoid possible over-temperature in the thermal protection.

APA, Harvard, Vancouver, ISO, and other styles

16

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 (July 28, 2009): 2957–69. http://dx.doi.org/10.1098/rsta.2008.0271.

Full text

Abstract:

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 in some detail and are validated against laboratory data—of which results from two cases are presented. These validated LES models are then applied to an annular multi-burner gas turbine combustor and a simplified scramjet combustor, for which some additional experimental data are available. For these cases, good agreement with the available reference data is obtained, and the LES predictions are used to elucidate the flow physics in such devices to further enhance our knowledge of these propulsion systems. Particular attention is focused on the influence of the combustion chemistry, turbulence–chemistry interaction, self-ignition, flame holding burner-to-burner interactions and combustion oscillations.

APA, Harvard, Vancouver, ISO, and other styles

17

Kang, Sang Hun, Yang Ji Lee, Soo Seok Yang, and Byungil Choi. "Effects of Flameholder Configurations on Combustion in Scramjet Engines." Journal of Propulsion and Power 28, no. 4 (July 2012): 739–46. http://dx.doi.org/10.2514/1.b34323.

Full text

APA, Harvard, Vancouver, ISO, and other styles

18

Li, Lantian. "Study on scramjet engines with complex inlet flow conditions." Journal of Physics: Conference Series 2030, no. 1 (September 1, 2021): 012025. http://dx.doi.org/10.1088/1742-6596/2030/1/012025.

Full text

APA, Harvard, Vancouver, ISO, and other styles

19

Mitani, Tohru, and Muneo Izumikawa. "Criteria for flame holding in H2-fueled scramjet engines." Proceedings of the Combustion Institute 28, no. 1 (January 2000): 689–95. http://dx.doi.org/10.1016/s0082-0784(00)80270-2.

Full text

APA, Harvard, Vancouver, ISO, and other styles

20

Rolim, Tiago C., and Paulo G. P. Toro. "Preliminary analysis of scramjet engines based on engineering models." Aerospace Science and Technology 47 (December 2015): 256–68. http://dx.doi.org/10.1016/j.ast.2015.09.010.

Full text

APA, Harvard, Vancouver, ISO, and other styles

21

Wang, Shirui. "Analysis and Possible Improvements of Scramjet Engines: The Effective Thrust and the Combustion Stability Problems." Theoretical and Natural Science 5, no. 1 (May 25, 2023): 204–9. http://dx.doi.org/10.54254/2753-8818/5/20230403.

Full text

Abstract:

The scramjet is the representative of the future jet engine, and it has irreplaceable advantages in terms of working performance and service life. Although it has been developed more than fifty years, there are many problems in the driven system of the scramjet engine. This paper mainly focuses on the problems of the effective thrust and the combustion stability. The research shows that how the pressure ratio affects the positive thrust and the combustion stability. Furthermore, this paper also shows that the elements which can affect the pressure ratio. The lower inlet air temperature is beneficial to enhance the thrust. According to the relevant research which apply the CJ detonation theorem to find the possible reason for the combustion instability. For the possible improvements, the research found that the engine thrust at different speed and the allowable maximum speed. The type of fuel and the reactivity of the fuel can influence the thrust.

APA, Harvard, Vancouver, ISO, and other styles

22

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

23

Kumar, Susheel, Krishna Murari Pandey, and Kaushal Kumar Sharma. "Recent developments in technological innovations in scramjet engines: A review." Materials Today: Proceedings 45 (2021): 6874–81. http://dx.doi.org/10.1016/j.matpr.2020.12.1086.

Full text

APA, Harvard, Vancouver, ISO, and other styles

24

Macheret, Sergey O., Mikhail N. Shneider, and Richard B. Miles. "Plasma-Assisted Fuel Atomization and Multipoint Ignition for Scramjet Engines." Journal of Propulsion and Power 36, no. 3 (May 2020): 357–62. http://dx.doi.org/10.2514/1.b37671.

Full text

APA, Harvard, Vancouver, ISO, and other styles

25

Kitamura, Eijiro, Tohru Mitani, Syuichi Watanabe, Noboru Sakuranaka, Masahiro Takahashi, and Goro Masuya. "Aerodynamic Tests of Scramjet Engines with Variable Mach Number Nozzle." JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 53, no. 617 (2005): 288–94. http://dx.doi.org/10.2322/jjsass.53.288.

Full text

APA, Harvard, Vancouver, ISO, and other styles

26

Gupta, M. Satyanarayana, and Muttangi Venuprasad. "CFD Analysis of Supersonic flow performance around a scramjet engines." IOP Conference Series: Materials Science and Engineering 455 (December 19, 2018): 012027. http://dx.doi.org/10.1088/1757-899x/455/1/012027.

Full text

APA, Harvard, Vancouver, ISO, and other styles

27

Gao, Jin, Ziyi Kang, Weiheng Sun, Youyin Wang, Junlong Zhang, and Wen Bao. "Feasibility and Performance Analysis of High-Energy-Density Hydrocarbon-Fueled Turboexpander Engine." Aerospace 10, no. 9 (August 25, 2023): 753. http://dx.doi.org/10.3390/aerospace10090753.

Full text

Abstract:

With the in-depth research on hypersonic aerodynamics and hypersonic propulsion technology, humans are growing closer to space travel. Recent studies have shown that the pre-cooled air-turborocket (ATR) or turboexpander engines are some of the potential propulsion methods for reusable space vehicles and single stage-to-orbit (SSTO) missions because they have a high specific impulse at low Mach numbers, which can overcome the problem of the “thrust gap” in turbine-based combined-cycle (TBCC) engines. The ATR engine needs an additional oxidizing agent and the turboexpander engine usually uses hydrogen as fuel, which has low energy density and poor safety. To address this problem, this paper proposed a high-energy-density (HED) hydrocarbon-fueled turboexpander engine, and its feasibility has been proven through a simplified thermodynamic model. Through detailed thermodynamic analysis based on the energy and pressure balance, this paper analyzed the performance characteristics of the engine to evaluate its capacity to work in a wide speed range at low Mach numbers. The results show that the endothermic hydrocarbon-fueled turboexpander engine has good specific impulse in Mach 0∼4 at an equivalence ratio of 0.7∼1.3, and the turboexpander engine can be combined with the dual-mode scramjet and become an efficient acceleration method for SSTO missions and the reusable spacecraft.

APA, Harvard, Vancouver, ISO, and other styles

28

Llobet, J. R., K. D. Basore, R. J. Gollan, and I. H. Jahn. "Experimental and numerical heat transfer from vortex-injection interaction in scramjet flowfields." Aeronautical Journal 124, no. 1280 (May 11, 2020): 1545–67. http://dx.doi.org/10.1017/aer.2020.39.

Full text

Abstract:

ABSTRACTAir-breathing propulsion has the potential to decrease the cost per kilogram for access-to-space, while increasing the flexibility of available low earth orbits. However, to meet the performance requirements, fuel-air mixing inside of scramjet engines and thermal management still need to be improved.An option to address these issues is to use intrinsically generated vortices from scramjet inlets to enhance fuel-air mixing further downstream, leading to shorter, less internal drag generating, and thus more efficient engines. Previous works have studied this vortex-injection interaction numerically, but validation was impractical due to lack of published experimental data. This paper extends upon these previous works by providing experimental data for a canonical geometry, obtained in the T4 Stalker Tube at Mach 8 flight conditions, and assesses the accuracy of numerical methodologies such as RANS CFD to predict the vortex-injection interaction.Focus is placed on understanding the ability of the numerical methodology to replicate the most important aspects of the vortex-injection interaction. Results show overall good agreement between the numerical and experimental results, as all major features are captured. However, limitations are encountered, especially due to a localised region of over predicted heat flux.

APA, Harvard, Vancouver, ISO, and other styles

29

Zhu, Chengxiang, Xu Zhang, Fan Kong, and Yancheng You. "Design of a Three-Dimensional Hypersonic Inward-Turning Inlet with Tri-Ducts for Combined Cycle Engines." International Journal of Aerospace Engineering 2018 (November 27, 2018): 1–10. http://dx.doi.org/10.1155/2018/7459141.

Full text

Abstract:

The operation of a propulsion system in terms of horizontal takeoff/landing and full-speed range serves as one of the main difficulties for hypersonic travelling. In the present work, a three-dimensional inward-turning inlet with tri-ducts for combined cycle engines is designed for the operation of three different modes controlled by a single rotational flap on the compression side, which efficiently simplifies the inlet structure and the flap control mechanism. At high flight speed between Mach 4 and 6, the pure scramjet mode is switched on, whereas both the ejector and the scramjet paths are open for a moderate Mach number between 2 and 4 with a larger throat area guaranteeing the inlet startability. In the low flight speed range with Mach number below 2, the additional turbojet path will be turned on to supply air for the turbine engine, whereas the other two paths remain open for spillage. Numerical simulations under different operation modes have proven the feasibility and good performance of the designed inlet, e.g., a nearly full mass flow ratio and a total pressure recovery around 0.5 can be achieved at the cruise speed. Meanwhile, the inlet works properly at low flight speeds which overcomes the typical starting problem of similar inlet designs. In the near future, wind tunnel experiments will be carried out to validate our inlet design and its performance.

APA, Harvard, Vancouver, ISO, and other styles

30

Kouchi, Toshinori, Tohru Mitani, Tetsuo Hiraiwa, Sadatake Tomioka, and Goro Masuya. "Evaluation of Thrust Performance in Scramjet Engines with Measured Internal Drag." JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 51, no. 595 (2003): 403–11. http://dx.doi.org/10.2322/jjsass.51.403.

Full text

APA, Harvard, Vancouver, ISO, and other styles

31

Kang, Sang Hun, Yang Ji Lee, Soo Seok Yang, Michael K. Smart, and Milinda V. Suraweera. "Cowl and Cavity Effects on Mixing and Combustion in Scramjet Engines." Journal of Propulsion and Power 27, no. 6 (November 2011): 1169–77. http://dx.doi.org/10.2514/1.48818.

Full text

APA, Harvard, Vancouver, ISO, and other styles

32

Mitani, Tohru, Noboru Sakuranaka, Sadatake Tomioka, and Kan Kobayashi. "Boundary-Layer Control in Mach 4 and Mach 6 Scramjet Engines." Journal of Propulsion and Power 21, no. 4 (July 2005): 636–41. http://dx.doi.org/10.2514/1.7978.

Full text

APA, Harvard, Vancouver, ISO, and other styles

33

Powell, O. A., J. T. Edwards, R. B. Norris, K. E. Numbers, and J. A. Pearce. "Development of Hydrocarbon-Fueled Scramjet Engines: The Hypersonic Technology (HyTech) Program." Journal of Propulsion and Power 17, no. 6 (November 2001): 1170–76. http://dx.doi.org/10.2514/2.5891.

Full text

APA, Harvard, Vancouver, ISO, and other styles

34

Tetlow, M. R., and C. J. Doolan. "Comparison of Hydrogen and Hydrocarbon-Fueled Scramjet Engines for Orbital Insertion." Journal of Spacecraft and Rockets 44, no. 2 (March 2007): 365–73. http://dx.doi.org/10.2514/1.24739.

Full text

APA, Harvard, Vancouver, ISO, and other styles

35

OGAWA, Hideaki, and Russell R. BOYCE. "1708 Numerical Investigation of Inlet Starting Methods for Axisymmetric Scramjet Engines." Proceedings of the Fluids engineering conference 2010 (2010): 493–94. http://dx.doi.org/10.1299/jsmefed.2010.493.

Full text

APA, Harvard, Vancouver, ISO, and other styles

36

Mitani, Tohru, Eijiro Kitamura, Syuichi Watanabe, Noboru Sakuranaka, Masahiro Takahashi, and Goro Masuya. "A Mach Number Sweep Nozzle and Aerodynamic Tests of Scramjet Engines." Proceedings of Autumn Conference of Tohoku Branch 2004.40 (2004): 75–76. http://dx.doi.org/10.1299/jsmetohoku.2004.40.75.

Full text

APA, Harvard, Vancouver, ISO, and other styles

37

Zhang, Silong, Yu Feng, Duo Zhang, Yuguang Jiang, Jiang Qin, and Wen Bao. "Parametric numerical analysis of regenerative cooling in hydrogen fueled scramjet engines." International Journal of Hydrogen Energy 41, no. 25 (July 2016): 10942–60. http://dx.doi.org/10.1016/j.ijhydene.2016.03.176.

Full text

APA, Harvard, Vancouver, ISO, and other styles

38

Hao, Xinyue, Juntao Chang, Wen Bao, and Zexu Zhang. "A model of mode transition logic in dual-mode scramjet engines." Aerospace Science and Technology 49 (February 2016): 173–84. http://dx.doi.org/10.1016/j.ast.2015.12.001.

Full text

APA, Harvard, Vancouver, ISO, and other styles

39

Hoste, J. J. O. E., M. Fossati, I. J. Taylor, and R. J. Gollan. "Characterisation of the eddy dissipation model for the analysis of hydrogen-fuelled scramjets." Aeronautical Journal 123, no. 1262 (March 27, 2019): 536–65. http://dx.doi.org/10.1017/aer.2018.169.

Full text

Abstract:

ABSTRACTThe eddy dissipation model (EDM) is analysed with respect to the ability to address the turbulence–combustion interaction process inside hydrogen-fuelled scramjet engines designed to operate at high Mach numbers (≈7–12). The aim is to identify the most appropriate strategy for the use of the model and the calibration of the modelling constants for future design purposes. To this end, three hydrogen-fuelled experimental scramjet configurations with different fuel injection approaches are studied numerically. The first case consists of parallel fuel injection and it is shown that relying on estimates of ignition delay from a 1D kinetics program can greatly improve the effectiveness of the EDM. This was achieved through a proposed zonal approach. The second case considers fuel injection behind a strut. Here the EDM predicts two reacting layers along the domain which is in agreement with experimental temperature profiles close to the point of injection but not the case any more at the downstream end of the test section. The first two scramjet test cases demonstrated that the kinetic limit, which can be applied to the EDM, does not improve the predictions in comparison to experimental data. The last case considered a transverse injection of hydrogen and the EDM approach provided overall good agreement with experimental pressure traces except in the vicinity of the injection location. The EDM appears to be a suitable tool for scramjet combustor analysis incorporating different fuel injection mechanisms with hydrogen. More specifically, the considered test cases demonstrate that the model provides reasonable predictions of pressure, velocity, temperature and composition.

APA, Harvard, Vancouver, ISO, and other styles

40

Ogawa, Hideaki, and Masatoshi Kodera. "Physical Insight into Fuel/Air Mixing with Hypermixer Injectors for Scramjet Engines." Journal of Propulsion and Power 31, no. 5 (September 2015): 1423–35. http://dx.doi.org/10.2514/1.b35638.

Full text

APA, Harvard, Vancouver, ISO, and other styles

41

Liang, Jianhan, Zhiqi Liu, and Yu Pan. "Flight Acceleration Effect on Heat Transfer Deterioration of Actively Cooled Scramjet Engines." Journal of Thermophysics and Heat Transfer 30, no. 2 (April 2016): 279–87. http://dx.doi.org/10.2514/1.t4704.

Full text

APA, Harvard, Vancouver, ISO, and other styles

42

Simone, D., and C. Bruno. "Preliminary Investigation on Lithium Hydride as Fuel for Solid-Fueled Scramjet Engines." Journal of Propulsion and Power 25, no. 4 (July 2009): 875–84. http://dx.doi.org/10.2514/1.39136.

Full text

APA, Harvard, Vancouver, ISO, and other styles

43

Mitani, Tohru, Tetsuo Hiraiwa, Yuichi Tarukawa, and Goro Masuya. "Drag and Total Pressure Distributions in Scramjet Engines at Mach 8 Flight." Journal of Propulsion and Power 18, no. 4 (July 2002): 953–60. http://dx.doi.org/10.2514/2.6022.

Full text

APA, Harvard, Vancouver, ISO, and other styles

44

Mitani, Tohru, Nobuo Chinzei, and Goro Masuya. "Mach 2.5 experiments of reaction quenching in gas sampling for scramjet engines." Symposium (International) on Combustion 27, no. 2 (January 1998): 2151–56. http://dx.doi.org/10.1016/s0082-0784(98)80063-5.

Full text

APA, Harvard, Vancouver, ISO, and other styles

45

Sen, Devendra, Apostolos Pesyridis, and Andrew Lenton. "A Scramjet Compression System for Hypersonic Air Transportation Vehicle Combined Cycle Engines." Energies 11, no. 6 (June 14, 2018): 1568. http://dx.doi.org/10.3390/en11061568.

Full text

APA, Harvard, Vancouver, ISO, and other styles

46

Hiraiwa, Tetsuo, Katsuhiro Ito, Shigeru Sato, Shuichi Ueda, Kouichiro Tani, Sadatake Tomioka, and Takeshi Kanda. "Recent progress in scramjet/combined cycle engines at JAXA, Kakuda space center." Acta Astronautica 63, no. 5-6 (September 2008): 565–74. http://dx.doi.org/10.1016/j.actaastro.2008.04.011.

Full text

APA, Harvard, Vancouver, ISO, and other styles

47

Bordoloi, Namrata, Krishna Murari Pandey, and Kaushal Kumar Sharma. "Numerical Investigation on the Effect of Inflow Mach Numbers on the Combustion Characteristics of a Typical Cavity-Based Supersonic Combustor." Mathematical Problems in Engineering 2021 (September 8, 2021): 1–14. http://dx.doi.org/10.1155/2021/3526454.

Full text

Abstract:

The air-breathing engines, commonly known as Supersonic Combustor Ramjet (SCRAMJET) engines, are one of the most prominent technologies among researchers due to their high thrust-to-weight ratio. The researchers are constantly making efforts for improved performance of the combustor under the required boundary conditions. The present working computational model studies a hydrogen-fueled parallel cavity scramjet combustor to recognize the complex flow field characteristics and performance of the combustor in Ansys 15.0. The computational model developed is a replica of an experiment conducted in China which slightly modified the boundary conditions. The standard two-equation K- ε turbulence model and Reynolds averaged Navier Stokes (RANS) equation with finite-rate/eddy dissipation species reaction model are used to simulate the problem. The validation of the present model is achieved by comparing the results with already available experimental data in conformity with the literature. The results of the simulations are in satisfactory accord with the experimental data and images. Furthermore, to achieve the stated objective, different incoming Mach numbers, namely, 2.25, 2.52, and 2.75, are considered for a more clear understanding of variables that affects the characteristics of the flow field. The temperature, Mach number, density pressure, and H2O mass fraction contours were studied to facilitate proper understanding. The maximum temperature rise observed is 2711.467 K for M = 2.25. Additionally, the performance parameters, namely, combustion and mixing efficiencies, are also studied. The maximum combustion and mixing efficiencies are 87.47% and 98.15% for M = 2.25 and 2.75, respectively.

APA, Harvard, Vancouver, ISO, and other styles

48

Blankson, I. M. "Air-Breathing Hypersonic Cruise: Prospects for Mach 4–7 Waverider Aircraft." Journal of Engineering for Gas Turbines and Power 116, no. 1 (January 1, 1994): 104–15. http://dx.doi.org/10.1115/1.2906779.

Full text

Abstract:

There is currently a renewal of world-wide interest in hypersonic flight. Vehicle concepts being considered range from cruise missiles to SSTO and TSTO vehicles. The new characteristics of these vehicles are that they will be powered by air-breathing engines and have long residence times in the air-breathing corridor. In the Mach 4–7 regime, waverider aircraft are being considered as candidates for both long-range and short-range cruise missions, as hypersonic missiles, and as high-L/D highly maneuverable vehicles. This paper will discuss the potential for near-term and far-term application of air-breathing engines to the above-mentioned waverider vehicle concepts and missions. In particular, the cruise mission is discussed in detail and attempts are made to compare and contrast it with the accelerator mission. Past criticisms levied against waveriders alleging low volumetric efficiency, lack of engine/airframe integration studies, poor off-design performance, poor take-off and landing capability, have been shown by ongoing research to be unfounded. A discussion is presented of some of the technical challenges and ongoing research aimed at realizing such vehicles: from turboramjet and scramjet technology development, propulsion-airframe integration effects on vehicle performance, aeroservothermoelastic systems analysis, hypersonic stability and control with aeroservothermoelastic and propulsion effects, etc. A unique and very strong aspect of hypersonic vehicle design is the integration and interaction of the propulsion system, aerodynamics, aerodynamic heating, stability and control, and materials and structures. This first-order multidisciplinary situation demands the ability to integrate highly coupled and interacting elements in a fundamental and optimal fashion to achieve the desired performance. Some crucial technology needs are found in propulsion-airframe integration and its role in configuration definition, hypersonic boundary-layer transition and its impact on vehicle gross-weight and mission success, scramjet combustor mixing length and its impact on engine weight and, CFD (turbulence modeling, transition modeling, etc) as a principal tool for the design of hypersonic vehicles. Key technology implications in thermal management, structures, materials, and flight control systems will also be briefly discussed. It is concluded that most of the technology requirements in the Mach 4–7 regime are relatively conventional, making cited applications near-term, yet offering very significant advancements in aircraft technology.

APA, Harvard, Vancouver, ISO, and other styles

49

Ispir, Ali Can, Pedro Miguel Gonçalves, and Bayindir H. Saracoglu. "Analysis of a combined cycle propulsion system for STRATOFLY hypersonic vehicle over an extended trajectory." MATEC Web of Conferences 304 (2019): 03001. http://dx.doi.org/10.1051/matecconf/201930403001.

Full text

Abstract:

Hypersonic civil aviation is an important enabler for extremely shorter flight durations for long-haul routes and using unexploited flight altitudes. Combined cycle engine concepts providing extended flight capabilities, i.e. propelling the aircraft from take-off to hypersonic speeds, are proposed to achieve high-speed civil air transportation. STRATOFLY project is a continuation of former European efforts in hypersonic research and aims at developing a commercial reusablevehicle for cruise speed of Mach 8 at stratospheric altitudes as high as 35 km above ground level. The propulsion plant of STRATOFLY aircraft consists of combination of two different type of engines: an array of air turbo rockets and a dualmode ramjet/scramjet. In the present study, 1D transient thermodynamic simulations for this combined cycle propulsion plant have been conducted between Mach 0 to 8 by utilizing 1D inviscid flow transport relations, numerical tools availablein EcosimPro software platform and the European Space Propulsion System Simulation libraries. The optimized engine parameters are achieved by coupling EcosimPro software with Computer Aided Design Optimization which is a differential evolution algorithm developed at the von Karman Institute.

APA, Harvard, Vancouver, ISO, and other styles

50

Kitamura, Eijiro, Tohru Mitani, Noboru Sakuranaka, Syuichi Watanabe, and Goro Masuya. "Evaluation of the Internal Drag of Scramjet Engines by Multi-Points Pressure Measuring." Proceedings of the Fluids engineering conference 2003 (2003): 56. http://dx.doi.org/10.1299/jsmefed.2003.56.

Full text

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!