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Relevant bibliographies by topics / Supersonic Transport

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Academic literature on the topic 'Supersonic Transport'

Author: Grafiati

Published: 4 June 2021

Last updated: 13 February 2022

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Journal articles on the topic "Supersonic Transport"

1

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

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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 (March 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 commercial transport projects in the time period between 1986 until about 1999, designs which did not proceed towards the production hardware stage. This study critically examines the anatomy of two generations of supersonic commercial transport design failures and successes in order to arrive at lessons learned free of ‘wishful thinking’. The design conditions leading to the identification of the product ‘solution space’ for an economically and environmentally acceptable supersonic commercial transport are discussed. Having assembled an understanding of the product metrics valid for supersonic commercial transports, the paper then provides an outlook for the first generation of supersonic corporate and cargo jet projects. This first generation of supersonic business jet (SSBJ) and supersonic cargo jet (SSCJ) projects spans a period of nearly two decades of development, starting from 1988 until today. The present study identifies that the product development metrics of this class of aircraft is radically different compared to the metrics valid for supersonic commercial transports. The challenges in VIP transportation and dedicated freight transportation at supersonic speeds are portrayed leading to two principal trains of thought targeting the development of the first supersonic business jet and/or supersonic cargo jet hardware: the development based on a new airframe, and alternatively the development based on an existing airframe.

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

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

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Kusunose, Kazuhiro, Daigo Maruyama, Kisa Matsushima, Kazuhiro Nakahashi, Hiroshi Yamashita, Masahito Yonezawa, and Shigeru Obayashi. "Toward silent supersonic transport—A fundamental study of supersonic biplane." Journal of the Acoustical Society of America 120, no. 5 (November 2006): 3078. http://dx.doi.org/10.1121/1.4787409.

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

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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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Guan, X. "Supersonic wing-body wave drag co-ordinated optimisation based on FCE methodology." Aeronautical Journal 118, no. 1209 (November 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 supersonic wing-body wave drag can be significantly reduced by the proposed method with relatively small numbers of design parameter. In the optimisation case presented in this paper a 45% wave drag reduction is achieved. The wave drag optimised configuration also achieved significant lift to drag ratio improvements in small angles-of-attack supersonic cruise flight conditions.

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Utomo, Muhammad Adnan, and Romie Oktavianus Bura. "Design of Inward-Turning External Compression Supersonic Inlet for Supersonic Transport Aircraft." INSIST 2, no. 2 (January 25, 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 desired design requirement. To investigate the intake design tool code and the performance of the generated intake shape, some CFD simulation were performed. The intake design tool code can be validated by comparing the shockwave location and the air properties in every intake's stations. The performance parameters that being observed are the intake efficiency, flow distortion level at the engine face, and the noise level generated by the shockwaves. The design tool written in MATLAB is working as intended. Two dimensional axisymmetric CFD simulations validation has been done and the design meets the minimum requirement. As for the 3D inlet geometry, with a little modification on diffuser and equipping vent to release the buildup pressure, the inlet has been successfully met the military standard on inlet performance (MIL-E-5007D). This design method also has feature to fit every possible throat cross sectional shapes and has been proven to work as designed.Keywords— Inward-turning, Supersonic, Engine Intakes, Low- noise, Design Method

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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 (September 28, 2016): 18–25. http://dx.doi.org/10.15407/tpwj2016.09.04.

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Dissertations / Theses on the topic "Supersonic Transport"

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Roughen, Kevin Michael. "Active aeroelastic control of supersonic transport aircraft." Diss., Restricted to subscribing institutions, 2009. http://proquest.umi.com/pqdweb?did=1998391981&sid=1&Fmt=2&clientId=1564&RQT=309&VName=PQD.

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Connolly, Joseph. "Aero-Propulso-Elastic Analysis of a Supersonic Transport." The Ohio State University, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=osu1543337967878799.

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Aleid, Louay. "Variable cycle propulsion systems for a supersonic civil transport." Thesis, Cranfield University, 1997. http://hdl.handle.net/1826/4433.

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The different aspects of overall performance of three variable cycle engines (VCE) candidates for future supersonic civil transport are analysed in this work. These aspects concern the design and off-design points performance, the airframe engine integration and variable geometry compressor and turbine design and performance. The three engines are compared to a traditional turbojet. The variable compressor maps were obtained with their running lines for the whole mission profile including the transition mode from medium býpass ratio to a lower bypass ratio turbofan. The specific fuel consumption (SFC) of the VCEs showed a significant improvement, especially at subsonic cruise, relative to a Turbojet engine. The extent of the variable geometry on the compressor stator angles, mixing area and the nozzle throat and exit areas is evaluated. The Fuel bill is estimated for two standard mission profiles. The effect of installation is estimated on an isolated nacelle. A sizing calculation is carried out for the whole nacelle including the intake and the nozzle. The drag due to the friction, pre-entry, afterbody and the shock waves is calculated in order to estimated the installed performance of the three engines. In the search of improving the VCE performance at subsonic cruise, the use of variable geometry at the low pressure turbine for the Turbofan-Turbojet engine is investigated. The effects of varying the LP turbine guide vanes stagger angle on the engine performance and component parameters are analysed. The turbine efficiency and non-dimensional mass flow changes due to the use of variable geometry are estimated. An updated version of the Turbornatch program was corrected and tested in order to study variable cycle engines, especially to simulate the transition from one mode to another.

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Steer, A. J. "Flight control for advanced supersonic transport aircraft handling quality design." Thesis, Cranfield University, 2001. http://dspace.lib.cranfield.ac.uk/handle/1826/11286.

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Concorde's unique low-speed handling qualities are acceptable when flown in a rigidly procedural manner by experienced pilots. However, to be commercially viable and environmentally acceptable more numerous second generation supersonic transport (SST) aircraft would have increased passenger carrying capacity, range and the flexibility to integrate with sub-sonic air traffic. Their much larger size, weight and inertia compared to Concorde's, combined with increasing levels of relaxed longitudinal stability to improve aerodynamic efficiency, results in unstable dynamics and degraded handling qualities on the final approach, where precise manual flightpath control is required. Modern fly-by-wire command and stability augmentation systems can restore stability, provide task tailored command laws and an associated level of handling qualities. Nonlinear Dynamic Inversion (NDI) enables control law prototyping and analysis for the rapid assessment, of conceptual designs to identify control power and command response requirements using both off-line and real-time simulation. This study has developed and applied NDI, and its realisable form (RNDI), in a novel way to design flight control laws specifically addressing handling quality requirements using selected criteria. Piloted validation has demonstrated that NDI pitch rate command will consistently provide Level 1 low-speed handling qualities in both steady and turbulent conditions. However, the best handling qualities can be achieved through a second order pitch rate response, generated by pre-filters, designed to author-suggested constraints on control anticipation parameter (CAP). The SST pitch rate criterion envelope, modified to ensure positive pitch attitude dropback, can then be applied to verify the time response. The resulting pre-filters are easily applied to RNDI inner loop controllers and would be straightforward to implement with simple and proven sensor requirements. Carefully designed NDI normal acceleration command laws are also capable of generating Level 1 low-speed handling qualities in steady conditions. However, their degraded performance in turbulence was exacerbated, relative to the pitch rate command laws, by the use of a fixed base simulator for pilot evaluation. Further motion based simulation studies would provide, in addition to pitching motion, the normal acceleration response cues necessary for a fair command law comparison to be made.

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Steer, Anthony J. "Flight control for advanced supersonic transport aircraft handling quality design." Thesis, Cranfield University, 2001. http://dspace.lib.cranfield.ac.uk/handle/1826/11286.

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Concorde's unique low-speed handling qualities are acceptable when flown in a rigidly procedural manner by experienced pilots. However, to be commercially viable and environmentally acceptable more numerous second generation supersonic transport (SST) aircraft would have increased passenger carrying capacity, range and the flexibility to integrate with sub-sonic air traffic. Their much larger size, weight and inertia compared to Concorde's, combined with increasing levels of relaxed longitudinal stability to improve aerodynamic efficiency, results in unstable dynamics and degraded handling qualities on the final approach, where precise manual flightpath control is required. Modern fly-by-wire command and stability augmentation systems can restore stability, provide task tailored command laws and an associated level of handling qualities. Nonlinear Dynamic Inversion (NDI) enables control law prototyping and analysis for the rapid assessment, of conceptual designs to identify control power and command response requirements using both off-line and real-time simulation. This study has developed and applied NDI, and its realisable form (RNDI), in a novel way to design flight control laws specifically addressing handling quality requirements using selected criteria. Piloted validation has demonstrated that NDI pitch rate command will consistently provide Level 1 low-speed handling qualities in both steady and turbulent conditions. However, the best handling qualities can be achieved through a second order pitch rate response, generated by pre-filters, designed to author-suggested constraints on control anticipation parameter (CAP). The SST pitch rate criterion envelope, modified to ensure positive pitch attitude dropback, can then be applied to verify the time response. The resulting pre-filters are easily applied to RNDI inner loop controllers and would be straightforward to implement with simple and proven sensor requirements. Carefully designed NDI normal acceleration command laws are also capable of generating Level 1 low-speed handling qualities in steady conditions. However, their degraded performance in turbulence was exacerbated, relative to the pitch rate command laws, by the use of a fixed base simulator for pilot evaluation. Further motion based simulation studies would provide, in addition to pitching motion, the normal acceleration response cues necessary for a fair command law comparison to be made.

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Teeple, Brian S. (Brian Scott). "Optimization of a mixer-ejector system for supersonic civilian transport aircraft." Thesis, Massachusetts Institute of Technology, 1998. http://hdl.handle.net/1721.1/50379.

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Pergamalis, Nikolaos. "Conceptual design, flying and handling qualities of a supersonic transport aircraft." Thesis, KTH, Flygdynamik, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-211167.

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The purpose of this project is the design of a supersonic aircraft that is able to meet the market’s requirements, be economically viable and mitigate the current barriers. The initial requirements of the design have been set according to the understanding obtained from a brief market research, taking into account the market needs, in addition to the economical and environmental restrictions. The conceptual design proposed is a supersonic transport able to execute transatlantic flights carrying 15 passengers. The aerodynamics, propulsion data and weight of the design have been estimated using empirical relations and experimental data found in references. The design has been evaluated regarding its performance, stability, flying and handling qualities. The relevant models have been created using the software Matlab, while the flight testing has been executed at the Merlin MP521 engineering flight simulator. Finally, a discussion is made about the environmental impact of the supersonic transport, focusing on the aerodynamic noise, generated by the sonic boom, and the air pollutants emissions.

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Giblette, Ted N. "Rapid Prediction of Low-Boom and Aerodynamic Performance of Supersonic Transport Aircraft Using Panel Methods." DigitalCommons@USU, 2019. https://digitalcommons.usu.edu/etd/7603.

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The Utah State University Aerolab developed and tested a set of tools for rapid prediction of the loudness of a sonic boom generated by supersonic transport aircraft. This work supported a larger effort led by Texas A&M to investigate the use of adaptive aerostructures in lowering sonic boom loudness at off design conditions. Successful completion of this effort will improve the feasibility of supersonic commercial transport over land. Funding was provided by a NASA University Leadership Initiative grant to several universities, including Utah State University, as well as industry partners to complete this work over a five year period. The work presented in this thesis was done over the first year of the grant. The Aerolab team was specifically tasked with developing a set of tools for rapidly predicting the sonic boom loudness of supersonic aircraft. Specifically, this work included an assessment of the existing analysis tools available followed by the planning, development, and testing of a framework of tools for performing the needed calculations. Results of the framework were compared against high fidelity solutions available from the 2017 AIAA Sonic Boom Prediction Workshop. These comparisons revealed that panel methods perform well for simple geometries. However, localized errors appear when modeling more complex geometries that reduce the accuracy of the predicted sonic boom loudness. It was found that these localized errors were a consequence of the inherent assumptions built into panel methods. Consequently, in future work, it may be necessary to develop techniques for combining the results of panel methods with higher fidelity methods or to revisit the panel method formulation.

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Guerriero, Vincenzo. "Experimental and numerical study of Coanda ejectors for pneumatic solid transport." Toulouse, INSA, 2008. http://eprint.insa-toulouse.fr/archive/00000311/.

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The transport of solid materials by means of pneumatic conveying is largely widespread in industry applications. The air flow generators for these systems may be turbines or fans, but more often, they are supersonic or Coanda ejectors as these devices do not present moving parts and thus associate reliability and durability. The Coanda effect ejectors are based on the phenomena of flow attachment to a curved wall (discovered by Henri Coanda in 1934). For this kind of ejector, the power is supplied by a high pressure reservoir (6-8 bars) which generates a jet via a sonic throat. The jet follows a curved wall and induces an important air flow which, amongst other things, makes it possible to transport solid particles. The main objective of the study presented in this thesis is to evaluate how a Coanda ejector could be used in the transport line of solid particles whose size and concentration (characterized by the ratio solid flow/air flow) would be variable. In a first part, the ejector has been studied alone, in the continuity of the work of Stéphane Orieux which contributed significantly to the increase in performances of this kind of device. Indeed, the geometrical parameters (section of the sonic throat, angle and length of the nozzle divergent part,. . . ) have a great influence on the induced flow for a given generating pressure. The flows inside the generator are complex (sonic, subsonic, supersonic) and the mixing zone which determines the induced flow is very sensitive to the ratios of the various sections. We have, by semi-analytical, numerical 2D and 3D and experimental (measurements by means of Pitot probe and PIV) approaches, contributed to a better knowledge of the physical mechanisms governing the operation of these devices and thus, developed tools helping in the design of COVAL ejectors, according to the selected particles transport problems. The second part of our work consisted in the study of the transport of solid matters. Again with the aim of an industrial utilization, we have developed a simplified analytical model, deduced from and summarizing numerous contributions presented in the literature. This model allows to calculate the pressure losses in a particles transport system, according to its configuration (sections, vertical and horizontal lines, bends. . . ) and to the operation conditions (particularly the ratio of mass flow rates of the solid particles and the conveying air) To validate this model, we have built up on the site of the COVAL company and with the assistance of its staff, a specific experimental device to carry out pressure and mass flow rate measurements that allow calculating the pressure losses according to the transported particles. Technical problems and time availability only allowed us to validate our model on linear sections of the transport line for particles diameters not exceeding 3 millimeters (the pipes diameter being of 46 mm) and for mass flow rate ratios (solid/gas) smaller than 2 hence for particles very dispersed in the air flow. This work performed in the framework of a University/Enterprise co-operation, and with the support from the European Commission through a Marie Curie Industry Host Fellowship, is a first approach that we think useful for our industrial partners. It also highlights the points to be developed as well on the theoretical level than on the experimental one for an optimization of particles transport systems based on the generators currently manufactured by the COVAL company
Le transport de matériaux solides au moyen d'un écoulement d’air est très répandu dans l'industrie. Les générateurs de ces écoulements peuvent être de type turbine ou soufflante, mais, de plus en plus, ce sont des éjecteurs à effet venturi ou à effet Coanda car ces derniers ne présentent pas de pièces mobiles et associent donc fiabilité et longévité. Les éjecteurs à effet Coanda sont basés sur l'effet d’attachement d'un écoulement à une paroi courbe (découvert par Henri Coanda en 1934). Ils utilisent comme source d'énergie un réservoir à haute pression (6-8 bars) qui génère un jet via un col sonique. Le jet suit une paroi courbe et entraîne un flux d'air important qui permet entre autre de transporter des particules solides. L'étude présentée dans cette thèse a pour objectif d'évaluer les possibilités d'utilisation d'un éjecteur à effet Coanda dans une ligne de transport de particules solides dont la taille et la concentration (caractérisée par le rapport débit solide/débit d’air) serait variable. Dans un premier temps, l'éjecteur a été étudié de façon isolée, dans la continuité des travaux de Stéphane Orieux qui a beaucoup contribué à l'amélioration des performances de ce dispositif. En effet, les paramètres géométriques (section du col sonique, angle et longueur du divergent…. ) ont une grande influence sur le débit entraîné pour une pression génératrice donnée. Les écoulements à l’intérieur du générateur sont en effet complexes (soniques, supersoniques puis subsoniques) et la zone de mélange qui détermine le flux entraîné est très sensible aux rapports des différentes sections. Nous avons par une approche semi analytique, numérique 2D et 3D et expérimentale (mesures au moyen de sonde de Pitot et PIV) contribué au développement de la connaissance des mécanismes physiques régissant le fonctionnement de ces dispositifs et ainsi, mis au point des outils d'aide à la conception des éjecteurs COVAL en fonction des problèmes choisis de transport de particules. La deuxième partie de notre travail a consisté en l’étude du transport de matières solides. Toujours dans l’esprit d’une utilisation industrielle, nous avons développé un modèle analytique simplifié s’inspirant et synthétisant de nombreux travaux présentés dans la littérature. Ce modèle permet de calculer la perte de charge d’un circuit de transport de particules en fonction de sa configuration (sections, lignes verticales et horizontales, coudes…) et des conditions de fonctionnement (particulièrement le rapport des débits massiques des particules solides et de l’air transporteur). Pour valider ce modèle, nous avons réalisé sur le site de la Société COVAL et avec l’aide des personnels de l’entreprise, un dispositif expérimental spécifique puis effectué des mesures de pression et de débit permettant de calculer les pertes de charge en fonction des particules transportées. Des contraintes techniques et de calendrier nous ont seulement permis de valider notre modèle sur des sections de conduites rectilignes pour des diamètres de particules ne dépassant pas 3 millimètres (le diamètre des conduites étant de 46 mm) et des rapports de débit masse solide/gaz inférieurs à 2 donc pour des particules très dispersées dans le flux d’air. Ce travail effectué dans le cadre d’une coopération Université/Entreprise, et grâce au soutient financier de la Commission Européenne dans le cadre d'une bourse Marie Curie d'accueil en entreprise, est une première approche que nous pensons utile à nos partenaires industriels. Il met également en évidence les points à développer tant sur le plan théorique qu’expérimental pour une optimisation du transport de particules en prenant pour base les générateurs actuellement fabriqués par la société COVAL

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Zang, Linge. "Study on Edge Fluctuation of Supersonic Molecular-Beam Fueled Plasmas Using Langmuir probes and Fast Cameras in Heliotron J." Kyoto University, 2014. http://hdl.handle.net/2433/188823.

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Books on the topic "Supersonic Transport"

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Ardema, Mark D. Optimization of supersonic transport trajectories. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1998.

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Roberts, Leonard. Computation of high speed transport aerodynamics. Stanford, Calif: Stanford University, Dept. of Aeronautics and Astronautics, 1991.

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Tavares, T. S. A supersonic fan equipped variable cycle engine for a Mach 2.7 supersonic transport. Cleveland, Ohio: Lewis Research Center, 1985.

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Iinkai, Sangyō Gijutsu Shingikai (Japan) Chōonsoku Yusōkiyō Suishin Shisutemu Hyōka. "Chōonsoku yusōkiyō suishin shisutemu" saishū hyōka hōkokusho. [Tokyo]: Sangyō Gijutsu Shingikai Hyōka Bukai Chōonsoku Yusōkiyō Suishin Shisutemu Hyōka Iinkai, 1999.

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Company, Douglas Aircraft. 1989 High-speed civil transport studies. Hampton, Va: Langley Research Center, 1991.

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Strack, William C. The challenges and opportunities of supersonic transport propulsion technology. [Washington, DC]: National Aeronautics and Space Administration, 1988.

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International, Workshop on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport (2000 Tokyo Japan). International Workshop on Numerical Simulation Technology for Design of Next Generation Supersonic Civil Transport: 17-19 January 2000, Tokyo. Tokyo, Japan: National Aerospace Laboratory, 2000.

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Lessard, Victor R. Analysis of a high speed civil transport configuration at subsonic flow conditions using a Navier-Stokes solver. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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Concorde: Le magnifique. Toulouse: Privat, 2008.

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Concorde and the Americans: International politics of the supersonic transport. Washington, D.C: Smithsonian Institution Press, 1997.

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Book chapters on the topic "Supersonic Transport"

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Velden, A. "Multi-Disciplinary Supersonic Transport Design." In New Design Concepts for High Speed Air Transport, 251–73. Vienna: Springer Vienna, 1997. http://dx.doi.org/10.1007/978-3-7091-2658-5_17.

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Velden, A. "Supersonic Aircraft Shape Optimization." In New Design Concepts for High Speed Air Transport, 237–50. Vienna: Springer Vienna, 1997. http://dx.doi.org/10.1007/978-3-7091-2658-5_16.

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Seebass, A. R. "The Prospects for Commercial Supersonic Transport." In New Design Concepts for High Speed Air Transport, 1–12. Vienna: Springer Vienna, 1997. http://dx.doi.org/10.1007/978-3-7091-2658-5_1.

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Traoré, Achmed, and Pascal Lemée. "Laminar Design for Supersonic Civil Transport." In Aerodynamic Drag Reduction Technologies, 141–53. Berlin, Heidelberg: Springer Berlin Heidelberg, 2001. http://dx.doi.org/10.1007/978-3-540-45359-8_16.

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Mertens, J. "Laminar Flow for Supersonic Transports." In New Design Concepts for High Speed Air Transport, 275–90. Vienna: Springer Vienna, 1997. http://dx.doi.org/10.1007/978-3-7091-2658-5_18.

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Mertens, J. "Certification of Supersonic Civil Transports." In New Design Concepts for High Speed Air Transport, 97–103. Vienna: Springer Vienna, 1997. http://dx.doi.org/10.1007/978-3-7091-2658-5_6.

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Foysi, Holger, and R. Friedrich. "Supersonic Turbulent Channel Flow with Passive Scalar Transport." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 350–57. Berlin, Heidelberg: Springer Berlin Heidelberg, 2004. http://dx.doi.org/10.1007/978-3-540-39604-8_44.

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Lovell, D. A. "European Research to Reduce Drag for Supersonic Transport Aircraft." In Aerodynamic Drag Reduction Technologies, 117–32. Berlin, Heidelberg: Springer Berlin Heidelberg, 2001. http://dx.doi.org/10.1007/978-3-540-45359-8_14.

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Kim, Hyoung-Jin, Daisuke Sasaki, Shigeru Obayashi, and Kazuhiro Nakahashi. "Aerodynamic Optimization of Supersonic Transport Wing Using Unstructured Adjoint Method." In Computational Fluid Dynamics 2000, 581–86. Berlin, Heidelberg: Springer Berlin Heidelberg, 2001. http://dx.doi.org/10.1007/978-3-642-56535-9_88.

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Velarde, M. G., W. Ebeling, and A. P. Chetverikov. "Anharmonic Oscillations, Dissipative Solitons and Non-Ohmic Supersonic Electric Transport." In Lecture Notes in Physics, 1–15. Berlin, Heidelberg: Springer Berlin Heidelberg, 2008. http://dx.doi.org/10.1007/978-3-540-78217-9_12.

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Conference papers on the topic "Supersonic Transport"

1

Windhorst, Robert, and Mark Ardema. "Supersonic transport trajectories." In 18th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-4247.

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Jensen, Daniel, Gerald Brines, and John Blanton. "Supersonic Transport (SST) Engines." In 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-4933.

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Ardema, Mark, and Robert Windhorst. "Optimization of supersonic transport trajectories." In Guidance, Navigation, and Control Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-4220.

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GALLOWAY, THOMAS, PAUL GELHAUSEN, MARK MOORE, and MARK WATERS. "Oblique wing supersonic transport concepts." In Guidance, Navigation and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-4230.

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Poling, Hugh, L. Robinson, Louis Sutherland, Hugh Poling, L. Robinson, and Louis Sutherland. "Supersonic transport secondary sonic booms." In 3rd AIAA/CEAS Aeroacoustics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-1659.

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6

Collard, Dudley. "Future Supersonic Transport Studies at Aerospatiale." In Aerospace Technology Conference and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1990. http://dx.doi.org/10.4271/901890.

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7

Seebass, A. "The prospects for commercial supersonic transport." In 32nd Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-17.

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8

USUKI, K., T. HIRAMOTO, T. UCHIDA, Y. SHIMOMURA, and K. INABA. "The conceptual study of supersonic transport structure." In Guidance, Navigation and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-4219.

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9

Li, Pei, Helmut Sobieczky, and Richard Seebass. "A design method for supersonic transport wings." In 13th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-1819.

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CHAMPAGNE, G. "Jet noise reduction concepts for the supersonic transport." In 9th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3328.

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Reports on the topic "Supersonic Transport"

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Grossman, A. S., D. E. Kinnison, J. E. Penner, K. E. Grant, J. Tamaresis, and P. S. Connell. O{sub 3} and stratospheric H{sub 2}O radiative forcing resulting from a supersonic jet transport emission scenario. Office of Scientific and Technical Information (OSTI), January 1996. http://dx.doi.org/10.2172/257417.

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2

Gates, W., and K. Sperber. Temporal behavior of tropical Pacific SST (supersonic transport) in the OSU (Oregon State University) coupled atmosphere: Upper ocean GCM (general circulation models). Office of Scientific and Technical Information (OSTI), February 1990. http://dx.doi.org/10.2172/7106559.

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