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Journal articles on the topic 'Scramjets'

Author: Grafiati

Published: 4 June 2021

Last updated: 6 September 2023

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1

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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2

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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3

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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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.

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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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5

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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6

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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7

Wagner, Timothy C., Walter F. O'Brien, G. Burton Northam, and James M. Eggers. "Plasma torch igniter for scramjets." Journal of Propulsion and Power 5, no. 5 (September 1989): 548–54. http://dx.doi.org/10.2514/3.23188.

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8

Jacobsen, Lance S., Campbell D. Carter, Thomas A. Jackson, Skip Williams, Jack Barnett, Daniel Bivolaru, Spencer Kuo, Chung-Jen Tam, and Robert A. Baurle. "Plasma-Assisted Ignition in Scramjets." Journal of Propulsion and Power 24, no. 4 (July 2008): 641–54. http://dx.doi.org/10.2514/1.27358.

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9

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.

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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.

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10

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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11

Anderson, Cody D., and Joseph A. Schetz. "Liquid-Fuel Aeroramp Injector for Scramjets." Journal of Propulsion and Power 21, no. 2 (March 2005): 371–74. http://dx.doi.org/10.2514/1.12238.

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12

Kimura, Toshiyuki, and Keisuke Sawada. "Three-Stage Launch System with Scramjets." Journal of Spacecraft and Rockets 36, no. 5 (September 1999): 675–80. http://dx.doi.org/10.2514/2.3500.

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13

Kumar, A., D. M. Bushnell, and M. Y. Hussaini. "Mixing augmentation technique for hypervelocity scramjets." Journal of Propulsion and Power 5, no. 5 (September 1989): 514–22. http://dx.doi.org/10.2514/3.23184.

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14

Fletcher, Edward A. "Scramjets and Surfboards: Some Forgotten History." Journal of Propulsion and Power 23, no. 1 (January 2007): 15–20. http://dx.doi.org/10.2514/1.21160.

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15

Jin, Xuan, Chibing Shen, and Xianyu Wu. "Numerical Study on Regenerative Cooling Characteristics of Kerosene Scramjets." International Journal of Aerospace Engineering 2020 (October 28, 2020): 1–12. http://dx.doi.org/10.1155/2020/8813929.

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The use of kerosene-based regenerative cooling for scramjet has been found widespread attention due to its inherent nature of high energy utilization efficiency and good thermal protection performance. In order to provide a reference for the later design and experiments, three-dimensional turbulence simulations and sensitivity analysis were performed to determine the effects of three operating mode parameters, heat flux, mass flow rate, and outlet pressure, on the regenerative cooling characteristics of kerosene scramjets. A single rectangular-shaped channel for regenerative cooling was assumed. The RNG k-ε turbulence model and kerosene cracking mechanism with single-step global reaction were applied for the supercritical-pressure heat transfer of kerosene flows in the channel. Conclusions can be drawn that as the kerosene temperature rises along the channel, the decrease of fluid density and viscosity contributes to increasing the fluid velocity and heat transfer. When the kerosene temperature is close to the pseudocritical temperature, the pyrolysis reaction results into the rapid increase of fluid velocity. However, the heat transfer deterioration occurs as the specific heat and thermal conductivity experience their turning points. The higher heat flux leads to lower heat transfer coefficient, and the latter stops rising when the wall temperature reaches the pseudocritical temperature. The same rising trend of the heat transfer coefficient is observed under different outlet pressures, but the heat transfer deterioration occurs earlier at smaller outlet pressure for the reason that the corresponding pseudocritical temperature decreases. The heat transfer coefficient increases significantly along with the rise of the mass flow rate, which is mainly attributable to the increase of Reynolds number. Quantitative results indicate that as the main influence factors, the heat flux and mass flow rate are respectively negatively and positively relative to the intensification of heat transfer, but outlet pressure always has little effects on cooling performance.

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16

Preller, Dawid, and Michael K. Smart. "Reusable Launch of Small Satellites Using Scramjets." Journal of Spacecraft and Rockets 54, no. 6 (November 2017): 1317–29. http://dx.doi.org/10.2514/1.a33610.

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17

Ogawa, Hideaki, Alexander L. Grainger, and Russell R. Boyce. "Inlet Starting of High-Contraction Axisymmetric Scramjets." Journal of Propulsion and Power 26, no. 6 (November 2010): 1247–58. http://dx.doi.org/10.2514/1.48284.

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18

Park, Chul, David Bogdanoff, and Unmeel B. Mehta. "Theoretical Performance of Frictionless Magnetohydrodynamic-Bypass Scramjets." Journal of Propulsion and Power 17, no. 3 (May 2001): 591–98. http://dx.doi.org/10.2514/2.5782.

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19

Stalker, R. J., A. Paull, D. J. Mee, R. G. Morgan, and P. A. Jacobs. "Scramjets and shock tunnels—The Queensland experience." Progress in Aerospace Sciences 41, no. 6 (August 2005): 471–513. http://dx.doi.org/10.1016/j.paerosci.2005.08.002.

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20

Chen, Hao, Mingming Guo, Ye Tian, Jialing Le, Hua Zhang, and Fuyu Zhong. "Intelligent reconstruction of the flow field in a supersonic combustor based on deep learning." Physics of Fluids 34, no. 3 (March 2022): 035128. http://dx.doi.org/10.1063/5.0087247.

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The data-driven intelligent reconstruction of a flow field in a supersonic combustor aids the real-time monitoring of wave system evolution in a scramjet flow field structure, allowing the determination of the combustion state for active flow control. In this paper, a deep learning architecture based on a multi-branch fusion convolutional neural network (MBFCNN) is proposed to reconstruct the flow field in a supersonic combustor. Experiments on hydrogen-fueled scramjets with different equivalence ratios were carried out in a direct-connected supersonic pulse combustion wind tunnel with an inflow Mach number of 2.5 to establish a dataset for MBFCNN network training and testing. The trained model successfully reconstructed the flow field structure from measured wall pressure data. The flow field reconstruction model provided a rich information source for the evolution of the wave system structure under the self-ignition conditions of the hydrogen-fueled scramjet, greatly improving the detection accuracy. The proposed deep learning architecture method was compared with basic convolutional neural network and symmetric convolutional neural network methods. The three methods all accurately reconstructed the flow field of the supersonic combustor. However, the proposed MBFCNN provided the best reconstruction results, and its average linear correlation coefficient in the test set was 0.952. The proposed MBFCNN had a lower mean square error and higher peak signal-to-noise ratio than the other two methods, which verified that the proposed model is eminently able to reconstruct and predict the flow field of a supersonic combustor.

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21

Liu, Qili, Damiano Baccarella, Brendan McGann, and Tonghun Lee. "Dual-Mode Operation and Transition in Axisymmetric Scramjets." AIAA Journal 57, no. 11 (November 2019): 4764–77. http://dx.doi.org/10.2514/1.j058391.

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22

Luo, Shibin, Dequan Xu, Jiawen Song, and Jian Liu. "A review of regenerative cooling technologies for scramjets." Applied Thermal Engineering 190 (May 2021): 116754. http://dx.doi.org/10.1016/j.applthermaleng.2021.116754.

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23

Simone, D., C. Bruno, and B. Hidding. "Silanes as Fuels for Scramjets and Their Applications." Journal of Propulsion and Power 22, no. 5 (September 2006): 1006–12. http://dx.doi.org/10.2514/1.18519.

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24

Timnat, Y. M. "Recent developments in ramjets, ducted rockets and scramjets." Progress in Aerospace Sciences 27, no. 3 (January 1990): 201–35. http://dx.doi.org/10.1016/0376-0421(90)90007-7.

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25

Rhoby, Michael R., Timothy M. Ombrello, N. Sebastian Okhovat, Amy M. Hansen, and Kevin C. Gross. "Infrared Hyperspectral Imaging Diagnostics of Fueling Strategy for Scramjets." Journal of Propulsion and Power 34, no. 6 (November 2018): 1391–400. http://dx.doi.org/10.2514/1.b36939.

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26

Zhou, Yue, and Pengfei Ju. "Effects of Wall Emissivity on Aerodynamic Heating in Scramjets." Fluid Dynamics & Materials Processing 16, no. 6 (2020): 1273–83. http://dx.doi.org/10.32604/fdmp.2020.09666.

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27

Gany, Alon. "ACCOMPLISHMENTS AND CHALLENGES IN SOLID FUEL RAMJETS AND SCRAMJETS." International Journal of Energetic Materials and Chemical Propulsion 8, no. 5 (2009): 421–46. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.v8.i5.40.

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28

Bricalli, Mathew G., Laurie Brown, Russell R. Boyce, and Tristan Vanyai. "Thermal and Mixing Efficiency Enhancement in Nonuniform-Compression Scramjets." AIAA Journal 57, no. 11 (November 2019): 4778–91. http://dx.doi.org/10.2514/1.j057908.

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29

Oran, Elaine S. "Matchsticks, Scramjets, and Black Holes: Numerical Simulation Faces Reality." AIAA Journal 40, no. 8 (August 2002): 1481–94. http://dx.doi.org/10.2514/2.1823.

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30

Yerra, Anasha. "Performance Enhancement of Single Expansion Ramp Nozzle in Scramjets." International Journal for Research in Applied Science and Engineering Technology 7, no. 7 (July 31, 2019): 1074–76. http://dx.doi.org/10.22214/ijraset.2019.7174.

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31

Tretyakov, P. K. "Organization of a pulsed mode of combustion in scramjets." Combustion, Explosion, and Shock Waves 48, no. 6 (November 2012): 677–82. http://dx.doi.org/10.1134/s0010508212060020.

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32

Jianping, Li, Song Wenyan, Xing Ying, and Luo Feiteng. "Influences of Geometric Parameters upon Nozzle Performances in Scramjets." Chinese Journal of Aeronautics 21, no. 6 (December 2008): 506–11. http://dx.doi.org/10.1016/s1000-9361(08)60167-3.

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33

Wang, JingYing, ZhenXun Gao, ChunHian Lee, and HuiQiang Zhang. "A decoupled procedure for convection-radiation simulation in scramjets." Science China Technological Sciences 57, no. 12 (November 15, 2014): 2551–66. http://dx.doi.org/10.1007/s11431-014-5706-y.

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34

Ren, Zhaoxin, Bing Wang, Gaoming Xiang, Dan Zhao, and Longxi Zheng. "Supersonic spray combustion subject to scramjets: Progress and challenges." Progress in Aerospace Sciences 105 (February 2019): 40–59. http://dx.doi.org/10.1016/j.paerosci.2018.12.002.

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35

Oran, E. S. "Matchsticks, scramjets, and black holes - Numerical simulation faces reality." AIAA Journal 40 (January 2002): 1481–94. http://dx.doi.org/10.2514/3.15222.

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36

Landsberg, Will O., Vincent Wheatley, Michael K. Smart, and Ananthanarayanan Veeraragavan. "Performance of high mach number scramjets - Tunnel vs flight." Acta Astronautica 146 (May 2018): 103–10. http://dx.doi.org/10.1016/j.actaastro.2018.02.031.

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37

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.

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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.

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38

Jacobsen, L. S., S. D. Gallimore, J. A. Schetz, and W. F. O’Brien. "Integration of an Aeroramp Injector/Plasma Igniter for Hydrocarbon Scramjets." Journal of Propulsion and Power 19, no. 2 (March 2003): 170–82. http://dx.doi.org/10.2514/2.6114.

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39

Ogawa, H., R. R. Boyce, A. Isaacs, and T. Ray. "Multi-Objective Design Optimisation of Inlet and Combustor for Axisymmetric Scramjets." Open Thermodynamics Journal 4, no. 1 (January 1, 2010): 86–91. http://dx.doi.org/10.2174/1874396x01004010086.

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40

Grossman, Peter M., Luca Maddalena, and Joseph A. Schetz. "Flush-Wall, Diamond-Shaped Fuel Injector for High Mach Number Scramjets." Journal of Propulsion and Power 24, no. 2 (March 2008): 259–66. http://dx.doi.org/10.2514/1.29956.

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41

Clark, Ryan J., and SO Bade Shrestha. "A review of numerical simulation and modeling of combustion in scramjets." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 229, no. 5 (June 30, 2014): 958–80. http://dx.doi.org/10.1177/0954410014541249.

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42

Yu, Kaikai, Jinglei Xu, Zheng Lv, and Guangtao Song. "Inverse design methodology on a single expansion ramp nozzle for scramjets." Aerospace Science and Technology 92 (September 2019): 9–19. http://dx.doi.org/10.1016/j.ast.2019.05.054.

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43

Ogawa, Hideaki, and Russell R. Boyce. "Nozzle Design Optimization for Axisymmetric Scramjets by Using Surrogate-Assisted Evolutionary Algorithms." Journal of Propulsion and Power 28, no. 6 (November 2012): 1324–38. http://dx.doi.org/10.2514/1.b34482.

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44

Vergine, Fabrizio, Cody Ground, and Luca Maddalena. "Strut Injectors for Scramjets: Total Pressure Losses in Two Streamwise Vortex Interactions." Journal of Propulsion and Power 33, no. 5 (September 2017): 1140–50. http://dx.doi.org/10.2514/1.b36306.

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45

Wang, Ning, Jin Zhou, Yu Pan, and Hui Wang. "Density Wave Instability of Supercritical Kerosene in Active Cooling Channels of Scramjets." Applied Mechanics and Materials 321-324 (June 2013): 293–98. http://dx.doi.org/10.4028/www.scientific.net/amm.321-324.293.

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Experimental investigations were made on the instability of supercritical kerosene flowing in active cooling channels. Two approaches were used to control the pressure in the channel. One is the back-pressure valve while the other is the venturi. In both conditions, a kind of low-frequency oscillation of pressure and temperature is observed. And the oscillation periods are calculated. By comparison with the flow time, it is concluded that the instability occurred in active cooling channels is probably one kind of density wave instability. And its period has no relationship with the cooling channel geometry, nor the pressure, but only depends on the flow time of kerosene in active cooling channels. When the mass flow rate, density and pressure drop couple with each other, the density wave instability will appear.

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46

Ben-Yakar, Adela, and Ronald K. Hanson. "Cavity Flame-Holders for Ignition and Flame Stabilization in Scramjets: An Overview." Journal of Propulsion and Power 17, no. 4 (July 2001): 869–77. http://dx.doi.org/10.2514/2.5818.

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47

Nordeen, Craig A., and Lee S. Langston. "There's a New Cycle in Town." Mechanical Engineering 140, no. 07 (July 1, 2018): 36–41. http://dx.doi.org/10.1115/1.2018-jul-2.

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The promises of increased efficiency, simplicity, and high power density are driving the current research focus on rotating detonation engines (RDEs). An engine that uses detonation rather than deflagration could have some key advantages. If harnessed in a gas turbine or rocket, detonation could reduce the need for some expensive hardware, lighten engine weight and increase power output and efficiency. Today, variants of the RDE as a combustor for gas turbines, rockets, and scramjets are being explored at the Air Force Research Laboratory (AFRL), Naval Research Laboratory, Naval Postgraduate School, and the Department of Energy. Similar work is being conducted in several other countries. This study provides a deeper look into RDEs.

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48

Frauholz, Sarah, Birgit U. Reinartz, Siegfried Müller, and Marek Behr. "Transition Prediction for Scramjets Using γ-Reθt Model Coupled to Two Turbulence Models." Journal of Propulsion and Power 31, no. 5 (September 2015): 1404–22. http://dx.doi.org/10.2514/1.b35630.

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49

Hirschen, C., and A. Gülhan. "Influence of Heat Capacity Ratio on Pressure and Nozzle Flow of a Scramjets." Journal of Propulsion and Power 25, no. 2 (March 2009): 303–11. http://dx.doi.org/10.2514/1.39380.

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50

Torrez, Sean M., James F. Driscoll, Matthias Ihme, and Matthew L. Fotia. "Reduced-Order Modeling of Turbulent Reacting Flows with Application to Ramjets and Scramjets." Journal of Propulsion and Power 27, no. 2 (March 2011): 371–82. http://dx.doi.org/10.2514/1.50272.

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