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Journal articles on the topic 'Supersonic Transport'

Author: Grafiati

Published: 4 June 2021

Last updated: 27 July 2025

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1

Chudoba, B., G. Coleman, A. Oza, and P. A. Czysz. "What price supersonic speed? A design anatomy of supersonic transportation Part 1." Aeronautical Journal 112, no. 1129 (2008): 141–51. http://dx.doi.org/10.1017/s0001924000002074.

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Abstract The first generation of supersonic commercial transportation has seen three serious attempts to arrive at an economically and environmentally viable aircraft. The US B2707-200/300 design was cancelled early before a prototype could emerge; the Russian Tu-144 design succeeded to become the first supersonic transport but spanned only a few years of restricted airline service; the Anglo-French Concorde endured more than 27 glamorous airline service years until the last of its species was retired on 30 August 2003. This first generation was followed by a second generation of supersonic co

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2

Davis, Lance A. "Supersonic Transport Redux?" Engineering 3, no. 6 (2017): 785–86. http://dx.doi.org/10.1016/j.eng.2017.12.008.

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3

Fournier, Gerard F. "Supersonic - Transport Takeoff Silencing." International Journal of Aeroacoustics 3, no. 3 (2004): 249–58. http://dx.doi.org/10.1260/1475472042887498.

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4

Bushnell, Dennis M. "Supersonic transport optimization concepts." Progress in Aerospace Sciences 146 (April 2024): 100993. http://dx.doi.org/10.1016/j.paerosci.2024.100993.

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5

Govindarajan, Nivedha, Abhinav Jayaswal, Katari Gaurav, and Aravind Seeni. "Higher-Fidelity CFD Tools for Conceptual Design of Supersonic Business Jets." ECS Transactions 107, no. 1 (2022): 515–32. http://dx.doi.org/10.1149/10701.0515ecst.

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Supersonic business jets are regarded as prime modes of next-generation supersonic transport. They allow long-distance travel at low duration by crossing the Mach 1 speed. This results in the breaking of the sound barrier and a sonic boom generated. Sonic boom and aerodynamic efficiency are the biggest concerns for the return of civil supersonic transport. Supersonic vehicles, such as spacecraft, high-speed missiles, and supersonic jets, are subjected to heavy shock wave drag during flight, which will seriously affect the aerodynamic performance of supersonic vehicles. In addition, supersonic

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6

Guan, X. "Supersonic wing-body wave drag co-ordinated optimisation based on FCE methodology." Aeronautical Journal 118, no. 1209 (2014): 1359–72. http://dx.doi.org/10.1017/s0001924000010010.

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Abstract Wave drag reduction is important for the aerodynamic performance optimisation of supersonic cruise aircrafts, such as the supersonic civil transport and the supersonic cruise missile. In this paper a method of the supersonic wing-body wave drag optimisation, the wave drag co-optimisation based on far-field composite elements (CoFCE), is proposed based on class-shape-transformation (CST) parameterisation. Wave drag optimisation cases of a supersonic civil transport wing-body are presented, including the optimisation results and computation cost analyses. It is suggested that the supers

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7

Fournier, Gerard F. "Can Supersonic Transport be Ultraquiet?" Journal of Aircraft 46, no. 2 (2009): 705–8. http://dx.doi.org/10.2514/1.39185.

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8

Kusunose, Kazuhiro, Daigo Maruyama, Kisa Matsushima, et al. "Toward silent supersonic transport—A fundamental study of supersonic biplane." Journal of the Acoustical Society of America 120, no. 5 (2006): 3078. http://dx.doi.org/10.1121/1.4787409.

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9

Joiner, Keith F., Jordan Zahra, and Obaid Rehman. "Conceptual sizing of next supersonic passenger aircraft from regression of the limited existing designs." MATEC Web of Conferences 198 (2018): 05001. http://dx.doi.org/10.1051/matecconf/201819805001.

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Despite previous versions, there are no current supersonic passenger transport aircraft. Much aircraft research is focused on hypersonic flight and the new technologies therein and is therefore unlikely to add to commercial versions anytime soon. This study re-examines conceptual sizing of a supersonic transport aircraft based on extant supersonic designs in order to ignite research into whether a commercially-viable design might exist. Key metrics are developed using distances between likely airport network nodes, an assumed number of passengers, and a reduction in transport time to one-third

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10

Kawanabe, Taichi, and Zhong Lei. "A Study on the Conceptual Design of a 50-Seat Supersonic Transport." Aerospace 12, no. 7 (2025): 625. https://doi.org/10.3390/aerospace12070625.

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The research and development of the next generation of supersonic transports (SSTs) meets economic and environmental problems. An SST encounters critical challenges, including the need for low fuel consumption, low noise, and low gas emissions. Currently, the feasibility of developing SSTs is increasing through the application of cutting-edge technologies, such as composite materials, advanced electric systems, sustainable aviation fuel, and innovative design methodologies. The object of this study was to perform the conceptual design of a 50-seat supersonic transport utilizing general concept

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11

Jones, R. T. "Technical Note–The flying wing supersonic transport." Aeronautical Journal 95, no. 943 (1991): 103–6. http://dx.doi.org/10.1017/s0001924000023630.

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The flying wing supersonic transport is simply a straight wing of high aspect ratio and of sufficient size to contain passengers comfortably. Such a wing can be steered to different sweep angles and thus adapted to efficient flight over a range of Mach numbers.The writer demonstrated such a wing by flying models at the First International Congress in the Aeronautical Sciences. The potential advantages of such a flying wing were discussed by G. H. Lee of Handley Page Aircraft at a subsequent Congress. The present paper gives recent studies of flight stability, efficiency and operational problem

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12

Windhorst, Robert, and Mark Ardema. "Some Characteristics of Supersonic Transport Trajectories." Journal of Aircraft 42, no. 4 (2005): 1079–80. http://dx.doi.org/10.2514/1.11940.

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13

HIRAKO, Keiichi. "National Experimental Supersonic Transport (NEXST-1)." Journal of the Society of Mechanical Engineers 107, no. 1024 (2004): 136–37. http://dx.doi.org/10.1299/jsmemag.107.1024_136.

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14

Kirz, Jochen, Susanne Bartels, Lothar Bertsch, et al. "Predicting Take-Off Noise, Sonic Boom, and Landing Noise of Supersonic Transport Aircraft Concepts." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 268, no. 1 (2023): 7288–97. http://dx.doi.org/10.3397/in_2023_1096.

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In 2023, the German Aerospace Center (DLR) has launched the STORMIE (Supersonic Transport Open Research Models and Impact on Environment) project. Focus of the project is the prediction and minimization of environmental and human impacts of civil supersonic transport. Data generated in the project will be used to inform national and European authorities in order to discuss certification standards for supersonic aircraft within the International Civil Aviation Organization's Committee on Aviation Environmental Protection (CAEP). In order to assess the environmental impacts, representative civil

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15

Xu, JiaKuan, Lei Qiao, and Junqiang Bai. "A CFD-Compatible Amplification Factor Transport Equation for Oblique Tollmien-Schlichting Waves in Supersonic Boundary Layers." International Journal of Aerospace Engineering 2020 (March 14, 2020): 1–12. http://dx.doi.org/10.1155/2020/3945463.

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Boundary layer transition is a hot research topic in fluid mechanics and aerospace engineering. In low-speed flows, two-dimensional Tollmien-Schlichting (T-S) waves always dominate the flow instability, which has been modeled by Coder and Maughmer from 2013. However, in supersonic flows, three-dimensional oblique Tollmien-Schlichting waves become dominant in flow instability. Inspired by Coder and Maughmer’s NTS amplification factor transport equation for two-dimensional Tollmien-Schlichting waves in low-speed flows and Kroo and Sturdza’s linear stability theory (LST) analysis results for obli

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16

Utomo, Muhammad Adnan, and Romie Oktavianus Bura. "Design of Inward-Turning External Compression Supersonic Inlet for Supersonic Transport Aircraft." INSIST 2, no. 2 (2019): 104. http://dx.doi.org/10.23960/ins.v2i2.90.

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Inward-turning external compression intake is one of the hybrid intakes that employs both external and internal compression intakes principle. This intake is commonly developed for hypersonic flight due to its efficiency and utilizing fewer shockwaves that generate heat. Since this intake employ less shockwaves, this design can be applied for low supersonic (Mach 1.4 - 2.5) intakes to reduce noise generated from the shockwaves while maintaining the efficiency. Other than developing the design method, a tool is written in MATLAB language to generate the intake shape automatically based on the d

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17

Li, Zhanke, Yang Liu, Yulin Ding, Zhijin Lei, and Boping Ma. "Influence of Quiet Spike on Supersonic Transport for Low Boom Effect." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 37, no. 1 (2019): 203–10. http://dx.doi.org/10.1051/jnwpu/20193710203.

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One of the biggest technical challenges of supersonic flight is the mitigation of sonic boom. To deal with this problem, the Gulfstream Aerospace Corporation came up with the spike concept, and it showed to be efficient. However, there also remain several problems, the first one is that installing the spike makes it harder to balance for supersonic transport and the another one is that the movement equipment is complex. In this paper, a new concept by replacing the multi-stage of the normal spike with smooth transistion cones is proposed. The concept simultaneously uses the CFD solver HUNS3D b

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18

Steer, A. J., and M. V. Cook. "Control and handling qualities considerations for an advanced supersonic transport aircraft." Aeronautical Journal 103, no. 1024 (1999): 265–72. http://dx.doi.org/10.1017/s0001924000064800.

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Abstract A future advanced supersonic transport aircraft (AST) has fundamental characteristics and problems inherent to supersonic cruise aircraft with corresponding unique control and handling characteristics. In order to optimise the aerodynamic performance across the full flight envelope a fully integrated flight and propulsion control system will be required. However, this will need to be designed from the outset within clearly defined flight control and performance guidelines. Relevant existing and AST specific handling qualities criteria will need to be developed if a successful commerci

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19

Chuvakhov, P. V., and I. V. Egorov. "TRANSITION OF SUPERSONIC BOUNDARY LAYER OVER AN UPSWEPT WING DUE TO ACOUSTIC NOISE." Доклады Российской академии наук. Физика, технические науки 509, no. 1 (2023): 63–66. http://dx.doi.org/10.31857/s2686740023020050.

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Results of direct numerical simulation of the receptivity of the supersonic boundary layer over an upswept wing with a thin parabolic profile to acoustic noise of various intensity are presented. Acoustic noise is shown to be capable of triggering laminar-turbulent transition over the upswept wing of supersonic transport.

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20

YUHARA, Tatsunori, and Kenichi RINOIE. "Feasibility Study of Hydrogen Fueled Supersonic Transport." AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 9 (2010): 29–35. http://dx.doi.org/10.2322/astj.9.29.

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21

Candel, Sebastien. "Concorde and the Future of Supersonic Transport." Journal of Propulsion and Power 20, no. 1 (2004): 59–68. http://dx.doi.org/10.2514/1.9180.

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22

Bain, Gordon M. "The Proposed U.S. Supersonic Commercial Air Transport." Annals of the New York Academy of Sciences 134, no. 1 (2008): 100–106. http://dx.doi.org/10.1111/j.1749-6632.1965.tb56145.x.

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23

HANAI, Toshio, Kenji YOSHIDA, Kenichirou USUKI, and Teiichi TAMAKI. "The current status of supersonic transport studies." Journal of the Japan Society for Aeronautical and Space Sciences 37, no. 430 (1989): 507–19. http://dx.doi.org/10.2322/jjsass1969.37.507.

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24

SWADLING, S. J. "Prospects for a second generation supersonic transport." Le Journal de Physique IV 03, no. C7 (1993): C7–11—C7–30. http://dx.doi.org/10.1051/jp4:1993702.

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25

Dmitriev, Sergey V., Nikolay N. Medvedev, Alexander P. Chetverikov, Kun Zhou, and Manuel G. Velarde. "Highly Enhanced Transport by Supersonic N -Crowdions." physica status solidi (RRL) - Rapid Research Letters 11, no. 12 (2017): 1700298. http://dx.doi.org/10.1002/pssr.201700298.

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26

Tsuchiya, Takao, and Masashi Kanamori. "Two-dimensional finite difference-time domain analysis of focus boom noise with velocity disturbance in the atmosphere." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, no. 6 (2021): 589–97. http://dx.doi.org/10.3397/in-2021-1576.

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In this paper, two-dimensional linear sound wave analysis in the stratified atmosphere with temperature gradient and velocity disturbance is numerically applied to the analysis and prediction of focus boom noise. Focus boom occurs when a supersonic transport accelerates or ascent or descent maneuvers at supersonic speed. Its overpressure is typically more than three times greater than that of a cruise sonic boom. As a result, supersonic transports in future commercial operation are likely to face restrictions on their flight conditions. The compact-explicit finite difference-time domain method

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27

Matthes, Sigrun, David S. Lee, Ruben Rodriguez De Leon, et al. "Review: The Effects of Supersonic Aviation on Ozone and Climate." Aerospace 9, no. 1 (2022): 41. http://dx.doi.org/10.3390/aerospace9010041.

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When working towards regulation of supersonic aviation, a comprehensive understanding of the global climate effect of supersonic aviation is required in order to develop future regulatory issues. Such research requires a comprehensive overview of existing scientific literature having explored the climate effect of aviation. This review article provides an overview on earlier studies assessing the climate effects of supersonic aviation, comprising non-CO2 effects. An overview on the historical evaluation of research focussing on supersonic aviation and its environmental impacts is provided, fol

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28

Spiller, P., and V. L. Varentsov. "New concept on the application of supersonic gas jets for space charge neutralized beam transport in an ICF reactor chamber." Laser and Particle Beams 15, no. 2 (1997): 231–33. http://dx.doi.org/10.1017/s0263034600010545.

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One of the most crucial problems of a heavy ion fusion (HIF) driver is the transport of the beam from the final focusing system to the fusion target. The conventional focusing scheme is based on ballistic transport, assuming that all space charge effects can be kept sufficiently small. To achieve a space charge neutralized beam transport, other more sophisticated schemes like beam transport in a plasma channel have been suggested. Inspired by the results of the first experiments on the generation of adequate discharge-driven plasmas, we suggest applying a pulsed supersonic gas jet for the high

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29

Huang, Shizhuo, Qian Chen, Yuwei Cheng, Jinyu Xian, and Zhengqi Tai. "Supersonic Combustion Modeling and Simulation on General Platforms." Aerospace 9, no. 7 (2022): 366. http://dx.doi.org/10.3390/aerospace9070366.

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Supersonic combustion is an advanced technology for the next generation of aerospace vehicles. In the last two decades, numerical simulation has been widely used for the investigation on supersonic combustion. In this paper, the modeling and simulation of supersonic combustion on general platforms are thoroughly reviewed, with emphasis placed on turbulence modeling and turbulence–chemistry interactions treatment which are both essential for engineering computation of supersonic combustion. It is found that the Reynolds-averaged Navier–Stokes methods on the general platforms have provided usefu

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30

Korzhik, V. N., N. P. Lyutik, A. A. Chajka, V. I. Tkachuk, I. D. Gos, and Yu A. Nikityuk. "Supersonic electric arc spraying of critical parts of rolling stock of railway transport." Paton Welding Journal 2016, no. 9 (2016): 18–25. http://dx.doi.org/10.15407/tpwj2016.09.04.

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31

Kazula, Stefan, Mark Wöllner, and Klaus Höschler. "Identification of efficient geometries for variable pitot inlets for supersonic transport." Aircraft Engineering and Aerospace Technology 92, no. 7 (2020): 981–92. http://dx.doi.org/10.1108/aeat-11-2019-0228.

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Purpose This paper aims to reveal the influence of selected geometric parameters on the aerodynamic performance of circular variable aero engine inlets in transonic and supersonic civil aviation. Design/methodology/approach The trade-off in inlet design and aerodynamic evaluation parameters is presented. The approach to investigate the dependencies between the aerodynamic and geometric parameters at different flight conditions by means of a parametric design study is introduced. Findings The dependencies of inlet drag and efficiency from geometric parameters at flight speeds of Mach 0.95 up to

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32

Kravchuk, V. V. "COMPARATIVE CHARACTERISTICS OF THE RESULTS OF ASSESSMENT OF PSYCHOPHYSIOLOGICAL FUNCTIONS OF DIFFERENT CATEGORIES OF MILITARY PILOTS." Fiziolohichnyĭ zhurnal 67, no. 5 (2021): 21–29. http://dx.doi.org/10.15407/fz67.05.021.

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The aim of the study was to carry out a comparative analysis of the values and structure of correlation relationships of psychophysiological function of different categories of military pilots (112 – supersonic, 109 – transport and 142 – helicopter aircraft). The analysis of the obtained results was carried out according to the indicators of personified characteristics, neurodynamic and psychomotor functions. A significant identity of the values and structure of the correlation relationships of indicators of psychophysiological functions of military pilots of supersonic and transport aviation

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33

McLeod, Andrew, Jan Palouš, and Anthony Whitworth. "Collisions of supersonic clouds." Proceedings of the International Astronomical Union 6, S270 (2010): 355–58. http://dx.doi.org/10.1017/s1743921311000627.

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AbstractWe present simulations of supersonic collisions between molecular clouds of mass 500 M⊙ and radius 2.24 pc. The simulations are performed with the SEREN SPH code. The code treats the energy equation and the associated transport of heating and cooling radiation. The formation of protostars is captured by introducing sink particles. Low velocity collisions form a shock-compressed layer which fragments to form stars. For high-velocity collisions, υrel ⪆ 5 km s−1, the non-linear thin shell instability strongly disrupts the shock-compressed layer, and may inhibit the formation of stars.

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34

Alendar, A. D., A. I. Lanshin, A. A. Evstigneev, K. Ya Yakubovsky, and M. V. Siluyanova. "The problems of creating a propulsion system of a new generation supersonic passenger aircraft (review)." VESTNIK of Samara University. Aerospace and Mechanical Engineering 22, no. 1 (2023): 7–28. http://dx.doi.org/10.18287/2541-7533-2023-22-1-7-28.

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The problems of creating a propulsion system for a new generation supersonic passenger aircraft are considered on the basis of a review of the work on the supersonic transport being carried out in the world. It is shown that the desire to achieve high flight performance and commercial effectiveness of a supersonic passenger aircraft while meeting up-to-date environmental requirements leads to contradictory technical solutions regarding the propulsion system: the location and number of engines, the scheme of the air intake and nozzle, the choice of the scheme and design parameters of the engine

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35

BOONJAIPETCH, Potsawat, Koji SHIMOYAMA, and Shigeru OBAYASHI. "Parametric Study on Waverider Configurations at Low-supersonic Speed for Low-boom Supersonic Transport." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 64, no. 6 (2021): 325–34. http://dx.doi.org/10.2322/tjsass.64.325.

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36

Aristov, V. V., A. A. Frolova, and S. A. Zabelok. "Supersonic Flows with Nontraditional Transport Described by Kinetic Methods." Communications in Computational Physics 11, no. 4 (2012): 1334–46. http://dx.doi.org/10.4208/cicp.110510.150511s.

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AbstractA new class of supersonic nonequilibrium flows is studied on the basis of solving the Boltzmann and model kinetic equations with the aim to consider new non-linear structures in open systems and to study anomalous transfer properties in relaxation zones. The Unified Flow Solver is applied for numerical simulations. Simple gases and gases with inner degrees of freedom are considered. The experimental data related to the influence of the so-called optical lattices on the supersonic molecular beams are considered and numerical analysis of the nonequilibrium states obtained on this basis i

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37

West, Thomas K., and Ben D. Phillips. "Multifidelity Uncertainty Quantification of a Commercial Supersonic Transport." Journal of Aircraft 57, no. 3 (2020): 491–500. http://dx.doi.org/10.2514/1.c035496.

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38

Connolly, Joseph W., George Kopasakis, Pawel Chwalowski, et al. "Aero-Propulso-Elastic Analysis of a Supersonic Transport." Journal of Aircraft 57, no. 4 (2020): 569–85. http://dx.doi.org/10.2514/1.c035531.

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39

Hallberg, Eric, and Isaac Kaminer. "Horizontal Control Effector Sizing for Supersonic Transport Aircraft." Journal of Guidance, Control, and Dynamics 22, no. 4 (1999): 618–22. http://dx.doi.org/10.2514/2.7639.

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40

Steer, A. J. "Supersonic transport aircraft longitudinal flight control law design." Aeronautical Journal 108, no. 1084 (2004): 319–29. http://dx.doi.org/10.1017/s000192400000018x.

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Abstract Modern civil transport aircraft utilise increasingly complex command and stability augmentation systems to restore stability, optimise aerodynamic performance and provide the pilot with the optimum handling qualities. Provided it has sufficient control power a second generation fly-by-wire supersonic transport aircraft should be capable of exhibiting similarly desirable low-speed handling qualities. However, successful flight control law design requires identification of the ideal command response type for a particular phase of flight, a set of valid handling quality design criteria a

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41

Freiherr, Greg. "Back to the Sound Barrier." Mechanical Engineering 138, no. 03 (2016): 36–41. http://dx.doi.org/10.1115/1.2016-mar-2.

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This article explores efforts that are being put into developing a business jet called AS2 and various challenges in developing the same. Aerion’s 12-seat tri-engine AS2, unveiled in spring 2014, is designed to have a range up to 5000 nautical miles; reach 51,000 feet; and cruise at speeds between Mach 1.2 and Mach 1.6. About the time it is ready to fly commercially, possibly as early as 2023, the market could support annual sales of 30 supersonic business jets. NASA and Lockheed Martin have been exploring a variety of options for quieting sonic booms. In its Strategic Implementation Plan, rel

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42

Mourouzidis, C., D. Del Gatto, S. Adamidis, et al. "Preliminary design of next generation Mach 1.6 supersonic business jets to investigate landing & take-off (LTO) noise and emissions – SENECA." Journal of Physics: Conference Series 2526, no. 1 (2023): 012011. http://dx.doi.org/10.1088/1742-6596/2526/1/012011.

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Abstract With the approach of next generation supersonic transport entry into service, new research activities were initiated to support updates on ICAO regulations and certification processes for supersonic transport vehicles. Within this context, the EU Horizon 2020 SENECA project has been launched to investigate the levels of noise and gaseous emissions in the vicinity of airports as well as the global climate impact of next generation supersonic civil aircraft. This paper introduces some of the preliminary outcomes of this investigation. It presents the preliminary design and performance a

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43

Julian Ooi, Hong Yee. "Aerodynamic Challenges and Innovations in Wing Designs for Supersonic Flight: A Comprehensive Review." International Journal of Science and Healthcare Research 9, no. 4 (2024): 454–63. https://doi.org/10.52403/ijshr.20240450.

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Supersonic flight has been of interest for decades due to the advantages it offers in speed and efficiency of transport, which are advantageous to both commercial and military aircraft. This paper covers a comprehensive review of various wing configurations for supersonic flight. We explore the aerodynamic and structural challenges associated with the various wing types. Supersonic flight offers significant benefits, but also poses complex engineering challenges including concerns with drag, stability, and sonic booms. This review examines the performance of straight, low-sweep, swept-back, de

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44

Nöding, Michel, Martin Schuermann, Lothar Bertsch, et al. "Simulation of Landing and Take-Off Noise for Supersonic Transport Aircraft at a Conceptual Design Fidelity Level." Aerospace 9, no. 1 (2021): 9. http://dx.doi.org/10.3390/aerospace9010009.

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The German Aerospace Center has launched an internal project to assess the noise impact associated with supersonic transport aircraft during approach and departure. A dedicated simulation process is established to cover all relevant disciplines, i.e., aircraft and engine design, engine installation effects, flight simulation, and system noise prediction. The core of the simulation process is comprised of methods at the complexity and fidelity level of conceptual aircraft design, i.e., typical overall aircraft design methods and a semi-empirical approach for the noise modeling. Dedicated interf

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45

Onilede, Moses Olushola. "Designing a Probable Engine for Future Supersonic Transport Aircraft." International Journal of Engineering and Advanced Technology 14, no. 3 (2025): 33–39. https://doi.org/10.35940/ijeat.c4565.14030225.

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Supersonic transport (SST) is poised to revolutionize the aviation industry once again, offering the potential for significantly reduced travel times across transcontinental and transoceanic routes. This paper delves into the key engine design elements for next-generation SST aircraft, focusing on critical areas such as fuel efficiency, environmental sustainability, and noise reduction. With a particular emphasis on low-bypass turbofan engines, variable cycle technology, and afterburner integration, this paper provides a comprehensive analysis of the technological advancements necessary to add

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46

Rogers, Helen, Hubert Teyssedre, Gianni Pitari, Volker Grewe, Peter van Velthoven, and Jostein Sundet. "Model intercomparison of the transport of aircraft-like emissions from sub- and supersonic aircraft." Meteorologische Zeitschrift 11, no. 3 (2002): 151–59. http://dx.doi.org/10.1127/0941-2948/2002/0011-0151.

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47

Sun, M. B., J. H. Liang, and Z. G. Wang. "A modified blending function for zonal hybrid Reynolds-averaged Navier—Stokes/large-eddy simulation methodology." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 223, no. 8 (2009): 1067–81. http://dx.doi.org/10.1243/09544100jaero575.

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A modified blending function for zonal hybrid Reynolds averaged Navier—Stokes/large eddy simulation (RANS/LES) methodology was developed using an empirical analogy from Menter k—ω shear stress transport (SST) turbulent model (Menter, 1994) to predict complex turbulent flows. Tests of slot jet in supersonic flow and supersonic flow over compression—expansion ramp was conducted and prediction of separations was well improved when certain model constant was forced on the traditional blending function (Baurle et al., 2003). Analysis based on calculations of flat plate boundary layer demonstrated t

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Proskurov, Stan, Markus Lummer, Jan Werner Delfs, et al. "Installed Fan Noise Simulation of a Supersonic Business Aircraft." Aerospace 10, no. 9 (2023): 773. http://dx.doi.org/10.3390/aerospace10090773.

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Overcoming the problem of excessive engine noise at low altitudes is a formidable task on the way to developing a supersonic passenger aircraft. The focus of this paper is on the fan noise shielding during take-off, investigated as part of the DLR project ELTON SST (estimation of landing and take-off noise of supersonic transport) for an in-house aircraft design. The supersonic inlet is required to provide the proper quantity and uniformity of air to the engine over a wider range of flight conditions than the subsonic inlet. For passenger aircraft, the noise problem influences engine integrati

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Moses, Olushola Onilede. "Designing a Probable Engine for Future Supersonic Transport Aircraft." International Journal of Engineering and Advanced Technology (IJEAT) 14, no. 3 (2025): 33–39. https://doi.org/10.35940/ijeat.C4565.14030225.

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<strong>Abstract: </strong>Supersonic transport (SST) is poised to revolutionize the aviation industry once again, offering the potential for significantly reduced travel times across transcontinental and transoceanic routes. This paper delves into the key engine design elements for next-generation SST aircraft, focusing on critical areas such as fuel efficiency, environmental sustainability, and noise reduction. With a particular emphasis on low-bypass turbofan engines, variable cycle technology, and afterburner integration, this paper provides a comprehensive analysis of the technological ad

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Aristov, V. V., I. V. Voronich, and S. A. Zabelok. "Study of Nonclassical Transport by Applying Numerical Methods for Solving the Boltzmann Equation." Журнал вычислительной математики и математической физики 63, no. 12 (2023): 2025–34. http://dx.doi.org/10.31857/s0044466923120050.

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This paper overviews the state of the art in the study of nonequilibrium gas flows with nonclassical transport, in which the Stokes and Fourier laws are violated (and, accordingly, the Chapman–Enskog method is inapplicable). For a reliable validation of anomalous transport effects, we use computational methods of different nature: the direct solution of the Boltzmann equation and direct simulation Monte Carlo. Nonclassical anomalous transport is manifested on scales of 5–10 mean free paths, which confirms the fact that a highly nonequilibrium flow is a prerequisite for the detection of the eff

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