Relevant bibliographies by topics / Supersonic flight

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Supersonic flight'

Author: Grafiati
Published: 4 June 2021
Last updated: 5 February 2022

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Journal articles on the topic "Supersonic flight"

1

Figat, Marcin, and Agnieszka Kwiek. "Aerodynamic optimisation of the rocket plane in subsonic and supersonic flight conditions." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 12 (August 14, 2017): 2266–81. http://dx.doi.org/10.1177/0954410017723672.

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This paper presents the results of a numerical study of the aerodynamic shape of the Rocket Plane LEX. The Rocket Plane is a main part of the Modular Airplane System – MAS; a special vehicle devoted to suborbital tourist flights. The Rocket Plane was designed for subsonic and supersonic flight conditions. Therefore, the impact of the Mach number should be considered during the aerodynamic design of the Rocket Plane. The main goal of the investigation was to determine the sensitivity of the Rocket Plane aerodynamic characteristics to the Mach number during the optimisation of the LEX geometry. The paper includes results of the optimisation process for Mach number from the range Ma = 0.5 to Ma = 2.5. These results reveal that the aerodynamic characteristics of models optimised for the subsonic and transonic regime of Mach numbers (up to Ma = 1) were also improved for the supersonic speed regime. However, in the case of models optimised for the supersonic flight regime the aerodynamic characteristics in subsonic flight regime, are inferior compared to the model before the optimisation process.
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Safronov, A. V., A. M. Syrotenko, B. Y. Semon, and A. N. Nedilko. "Mathematical model of fuselage oscillations at transonic flight speeds." Kosmìčna nauka ì tehnologìâ 27, no. 2 (May 17, 2021): 28–37. http://dx.doi.org/10.15407/knit2021.02.028.

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Ensuring the safety of supersonic aircraft flights and aerospace systems in the transonic range of M flight numbers still remains an urgent scientific and applied problem. This is caused by the peculiarities of the aerodynamic surfaces flow by inhomogeneous (transonic) air and is due to the emergence of various aeroelastic phenomena in these flight modes and the current lack of a generally accepted model of transonic flutter, even for aerodynamic control surfaces. Based on a joint analysis of the conditions for the formation of shock waves on the surface of the aerodynamic profile, changes in the parameters of supersonic flow across the Prandtl-Meyer expansion fan, and the hypothesis of "dynamic curvature of the aerodynamic profile", the approximate laws of interaction of elastic bending vibrations of the fuselage with fluctuations in shock waves were obtained. The obtained regularities are used to substantiate a mathematical model for estimating excited forces and excited bending moments of the fuselage. The analysis of the obtained mathematical model confirms the theoretical possibility of the appearance of fuselage forms of transonic flutter in supersonic aircraft, which was observed in the flight experiment and which is due to the interaction of shock waves with the angular velocity of the fuselage elastic bending vibrations. With the accepted in the article input geometrical data of a fuselage aerodynamic surfaces’ profile, the maximum possible values of fuselage bending moments are obtained using the developed mathematical model. The obtained mathematical model can be used for a preliminary approximate assessment of the transonic flutter fuselage forms characteristics in supersonic aircraft and aerospace systems.
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MIZOBATA, Kazuhide, Yoshihiro SUZUKI, Sakae OOISHI, Satoshi KONDOH, Takakage ARAI, and Kazuyuki HIGASHINO. "Aerodynamics and Flight Capability of a Supersonic Flight Experiment Vehicle." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 14, ists30 (2016): Pg_1—Pg_8. http://dx.doi.org/10.2322/tastj.14.pg_1.

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Petrescu, Relly Victoria Virgil. "About Supersonic Flight and Mach 3 Flying." American Journal of Engineering and Applied Sciences 13, no. 3 (March 1, 2020): 451–76. http://dx.doi.org/10.3844/ajeassp.2020.451.476.

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MERDA, Tomasz MERDA. "SEMI STABLE FLIGHT OF SUPERSONIC MORTAR PROJECTILE." PROBLEMY TECHNIKI UZBROJENIA 149, no. 1 (August 28, 2019): 23–46. http://dx.doi.org/10.5604/01.3001.0013.3769.

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Significantly large dispersion of projectiles was observed at firing a specific type of a supersonic mortar projectile being devel-oped in the frame of RAK ANUNICJA program. The flying paths, parameters and reasons of falling points dispersion were determined for tested projectiles with a model of external ballistics describing the projectile as a rigid body. Analysis of received results has indicated that the dispersion was not caused by an aerodynamic jump but by an effect which has not been described yet in the literature and is named here as “projectile’s semi-stable flight”. The paper includes a description of the effect with reasons and parameters affecting its occurrence, and a method for determination of the equilibrium nutation angle which plays a key role in this effect.
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Bashkirov, I., and O. Ogorodnikov. "Supersonic cruise flight of Vth generation fighters." Aerospace Systems 1, no. 2 (November 21, 2018): 121–27. http://dx.doi.org/10.1007/s42401-018-0007-y.

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Smart, M. "Scramjets." Aeronautical Journal 111, no. 1124 (October 2007): 605–19. http://dx.doi.org/10.1017/s0001924000004796.

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Abstract The supersonic combustion ramjet, or scramjet, is the engine cycle most suitable for sustained hypersonic flight in the atmosphere. This article describes some of the challenges facing scramjet designers, and the methods currently used for the calculation of scramjet performance. It then reviews the HyShot 2 and Hyper-X flight programs as examples of how sub-scale flights are now being used as important steps towards the development of operational systems. Finally, it describes some recent advances in three-dimensional scramjets with application to hypersonic cruise and multi-stage access-to-space vehicles.
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B Saheby, Eiman, Xing Shen, and Anthony P. Hays. "Design and performance study of a parametric diverterless supersonic inlet." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 2 (September 24, 2019): 470–89. http://dx.doi.org/10.1177/0954410019875384.

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Diverterless supersonic inlet integration for a flight vehicle requires a three-dimensional compression surface (bump) design with an acceptable shock structure and boundary layer diversion; this results in a low drag induction system with acceptable propulsive efficiency. In this investigation, a computational fluid dynamics-based-generated bump is used to design an integrated diverterless supersonic inlet without any bleed mechanism on a forebody with a large wetted area. Numerical solution of the Navier–Stokes equations simulates the flow pattern of the configuration. The forebody design analysis includes simulating the effects of angle of attack and sideslip by dependent computational domains. Results demonstrate the ability of the bump surface to keep the shock structures in an operational mode even at high supersonic angles of attack. Analysis of shock structures and shock wave boundary layer interactions at supersonic maneuver conditions indicate that the aerodynamic efficiency of the diverterless supersonic inlet in conditions with a thick boundary layer and high angles of attack is sufficient to ensure operation throughout the supersonic flight envelope.
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Steer, A. J. "Supersonic transport aircraft longitudinal flight control law design." Aeronautical Journal 108, no. 1084 (June 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 and piloted simulation evaluation tasks and metrics. A non-linear mathematical model of the European supersonic transport aircraft has been synthesized on the final approach to land. Specific handling quality design criteria have been proposed to enable the non-linear dynamic inversion flight control laws to be designed, with piloted simulation used for validation. A pitch rate command system, with dynamics matched to the aircraft’s flight path response, will consistently provide Level 1 handling qualities. Nevertheless, pre-filtering the pilot’s input to provide a second order pitch rate response, using the author’s suggested revised constraints on the control anticipation parameter will generate the best handling qualities during the terminal phase of flight. The resulting pre-filter can be easily applied to non-linear dynamic inversion inner loop controllers and has simple and flight proven sensor requirements.
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Steer, A. J., and M. V. Cook. "Control and handling qualities considerations for an advanced supersonic transport aircraft." Aeronautical Journal 103, no. 1024 (June 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 commercial transport aircraft is to be produced. This paper begins by presenting an overview of existing supersonic transport (SST) aircraft operations and current second generation SST research activities and design considerations. This is followed by an analysis of the principal aerodynamic, dynamic and control characteristics of SST and AST aircraft and their effect on the aircraft’s handling qualities. Finally, some possible solutions to the control and handling issues are investigated, assessed and presented.
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Dissertations / Theses on the topic "Supersonic flight"

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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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Jones, Anna Elizabeth. "Some problems in the numerical modelling of the lower stratosphere." Thesis, University of Cambridge, 1993. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.260379.

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Marklund, Hanna. "Supersonic Retro Propulsion Flight Vehicle Engineering of a Human Mission to Mars." Thesis, Luleå tekniska universitet, Rymdteknik, 2019. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-75820.

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A manned Mars mission will require a substantial increase in landed mass compared to previous robotic missions, beyond the capabilities of current Entry Descent and Landing, EDL, technologies, such as blunt-body aeroshells and supersonic disk-gap-band parachutes. The heaviest payload successfully landed on Mars to date is the Mars Science Laboratory which delivered the Curiosity rover with an approximate mass of 900 kg. For a human mission, a payload of magnitude 30-50 times heavier will need to reach the surface in a secure manner. According to the Global Exploration Roadmap, GER, a Human Mission to Mars, HMM, is planned to take place after year 2030. To prepare for such an event several technologies need maturing and development, one of them is to be able to use and accurately asses the performance of Supersonic Retro Propulsion, SRP, another is to be able to use inflatable heat shields. This internal study conducted at the European Space Agency, ESA, is a first investigation focusing on the Entry Descent and Landing, EDL, sequence of a manned Mars lander utilising an inflatable heatshield and SRP, which are both potential technologies for enabling future landings of heavy payloads on the planet. The thesis covers the areas of aerodynamics and propulsion coupled together to achieve a design, which considers the flight envelope constraints imposed on human missions. The descent has five different phases and they are defined as circular orbit, hypersonic entry, supersonic retropropulsion, vertical turn manoeuvre and soft landing. The focus of this thesis is on one of the phases, the SRP phase. The study is carried out with the retro-thrust profile and SRP phase initiation Mach number as parameters. Aerodynamic data in the hyper and supersonic regime are generated using Computational Fluid Dynamics, CFD, to accurately assess the retropropulsive performance. The basic concept and initial sizing of the manned Mars lander builds on a preliminary technical report from ESA, the Mission Scenarios and Vehicle Design Document. The overall optimisation process has three parts and is based on iterations between the vehicle design, CFD computations in the software DLR-Tau and trajectory planning in the software ASTOS. Two of those parts are studied, the vehicle design and the CFD,to optimise and evaluate the feasibility of SRP during the descent and test the design parameters of the vehicle. This approach is novel, the efficiency and accuracy of the method itself is discussed and evaluated. Initially the exterior vehicle Computer Aided Design, CAD, model is created, based on the Mission Scenarios and Vehicle Design Document, however updated and furthered. The propulsion system is modelled and evaluated using EcosimPRO where the nozzle characteristics, pressure levels and chemistry are defined, and later incorporated in the CAD model. The first iteration of the CFD part has an SRP range between Mach 7 and 2, which results in an evaluation of five points on the trajectory. The thrust levels, the corresponding velocity, altitude and atmospheric properties at those points can then be evaluated and later incorporated in ASTOS. ASTOS, in turn, can simulate the full trajectory from orbit to landing including the CFD data of the SRP phase. Due to time limitation only one iteration of the vehicle design and the SRP range was completed. However, the goals of the study were reached. A first assessment of SRP in Mars atmosphere has been carried out, and the aerodynamic and propulsive data has been collected to be built on in the future. The results indicate that the engines can start at a velocity of Mach 7. They also show consistency with similar studies conducted in Earths atmosphere. The current vehicle design, propulsion system and SRP range can now be furthered, updated and advanced in order to optimise the different descent phases in combination with future results from ASTOS.
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Fagin, Maxwell H. "Payload mass improvements of supersonic retropropulsive flight for human class missions to Mars." Thesis, Purdue University, 2016. http://pqdtopen.proquest.com/#viewpdf?dispub=10046736.

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Supersonic retropropulsion (SRP) is the use of retrorockets to decelerate during atmospheric flight while the vehicle is still traveling in the supersonic/hypersonic flight regime. In the context of Mars exploration, subsonic retropropulsion has a robust flight heritage for terminal landing guidance and control, but all supersonic deceleration has, to date, been performed by non-propulsive (i.e. purely aerodynamic) methods, such as aeroshells and parachutes.

Extending the use of retropropulsion from the subsonic to the supersonic regime has been identified as an enabling technology for high mass humans-to-Mars architectures. However, supersonic retropropulsion still poses significant design and control challenges, stemming mainly from the complex interactions between the hypersonic engine plumes, the oncoming air flow, and the vehicle’s exterior surface. These interactions lead to flow fields that are difficult to model and produce counter intuitive behaviors that are not present in purely propulsive or purely aerodynamic flight.

This study will provide an overview of the work done in the design of SRP systems. Optimal throttle laws for certain trajectories will be derived that leverage aero/propulsive effects to decrease propellant requirements and increase total useful landing mass. A study of the mass savings will be made for a 10 mT reference vehicle based on a propulsive version of the Orion capsule, followed by the 100 mT ellipsoid vehicle assumed by NASA’s Mars Design Reference Architecture.

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Simsek, Bugra. "Ablation Modeling Of Thermal Protection Systems Of Blunt-nosed Bodies At Supersonic Flight Speeds." Master's thesis, METU, 2013. http://etd.lib.metu.edu.tr/upload/12615414/index.pdf.

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The objective of this thesis is to predict shape change due to ablation and to find temperature distribution of the thermal protection system of a supersonic vehicle under aerodynamic heating by using finite element method. A subliming ablative is used as thermal protection material. Required material properties for the ablation analyses are found by using DSC (Differential Scanning Calorimetry) and TGA (Thermogravimetric Analysis) thermal analysis techniques. DSC is a thermal analysis technique that looks at how a material'
s specific heat capacity is changed by temperature and TGA is a technique in which the mass of a substance is monitored as a function of temperature. Moreover, oxyacetylene ablation tests are conducted for the subliming ablative specimens and measured recession values are compared with the analytically calculated values. Maximum difference between experimental results and analytical results is observed as 3% as seen in Table 7. For the finite element analyses, ANSYS Software is used. A numerical algorithm is developed by using programming language APDL (ANSYS Parametric Design Language) and element kill feature of ANSYS is used for simulation of ablation process. To see the effect of mesh size and time step on the solution of analyses, oxyacetylene test results are used. Numerical algorithm is also applied to the blunt-nosed section of a supersonic rocket which is made from subliming ablative material. Ablation analyses are performed for the nose section because nose recession is very important for a rocket to follow the desired trajectory and nose temperature is very important for the avionics in the inner side of the nose. By using the developed algorithm, under aerodynamic heating, shape change and temperature distribution of the nose section at the end of the flight are obtained. Moreover, effects of ablation on the trajectory of the rocket and on the flow around the rocket are examined by Missile DATCOM and CFD (computational fluid dynamics) analysis tools.
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Nacheva, Nadezhda, and Gijs Heldens. "The next generation of commercial supersonic flight : understanding the industry and the consumer perspectives." Thesis, Internationella Handelshögskolan, Högskolan i Jönköping, IHH, Företagsekonomi, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:hj:diva-39682.

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For decades, the speed of commercial aviation was constrained by the sound barrier. However, recent noticeable growth in air traffic and the recognition of the “time” as a valuable asset for passengers, call for more efficient, faster commercial transport. The commercial supersonic flight, able to fly above the speed of the sound has not been around ever since Concorde made its last trip in 2003, but it is promised to be on its way back. Currently, several existing and emerging companies are competing to revive the concept by developing and launching efficient supersonic plane between 2020-2025. The aircraft could operate on long-haul intercontinental flights about 2.6 times faster than current subsonic airplanes, targeting primarily business travelers. However, such a technological leapfrogging innovation embodies several engineering, economic, environmental and other factors, vital for its commercial success.                                The overall purpose of this master thesis is to investigate which factors could ensure the success of the upcoming supersonic commercial flight. The research will examine whether the new generation of supersonic planes can achieve maintainable commercial success by introducing industry expert opinions and exploring the perceptions of potential passengers towards supersonic flight as a possible future transportation mode.                               The limited literature on the subject created the need for descriptive research to expand the understanding. The chosen deductive approach relies on adopting the theoretical conceptions on the Theory of Disruptive Innovation and the Extended GAP Model of Service Quality. Pragmatic research philosophy is used due to the fact that it was deemed necessary to pursue multiple views to enable best answering the research questions. Qualitative interviews with ten industry experts have been conducted, capturing both the market specifications and the technical functions of the planes. Furthermore, 28 potential consumers who have flown in a business class on a long-haul flight gave valuable insights on the service quality perceptions.                                The results show that demand for supersonic flight exists and people are willing to use it as long as the plane satisfies their expectations of service quality. Based on the predictions of industry experts and the high level of curiosity of the potential customers interviewed, and their positive perceptions towards using it, the commercial  supersonic flight has the scale possibility to be highly successful. However, the upcoming supersonic aircraft should find a balance between the main service quality attributes, such as speed, comfort, convenience, and safety, in relation to the economic, environmental, and engineering challenges.
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Rabadán, Santana Edder José [Verfasser]. "Numerical Investigation of a Generic Supersonic Combustion Chamber under Realistic Flight Conditions / Edder José Rabadán Santana." München : Verlag Dr. Hut, 2015. http://d-nb.info/1074063570/34.

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Smith, Theodore Brooke. "Development and Ground Testing of Direct Measuring Skin Friction Gages for High Enthalpy Supersonic Flight Tests." Diss., Virginia Tech, 2001. http://hdl.handle.net/10919/29351.

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A series of direct-measuring skin friction gages were developed for a high-speed, high-temperature environment of the turbulent boundary layer in flows such as that in supersonic combustion ramjet (scramjet) engines, with a progression from free-jet ground tests to a design for an actual hypersonic scramjet-integrated flight vehicle. The designs were non-nulling, with a sensing head that was flush with the model wall and surrounded by a small gap. Thus, the shear force due to the flow along the wall deflects the head, inducing a measurable strain. Strain gages were used to detect the strain. The gages were statically calibrated using a direct force method. The designs were verified by testing in a well-documented Mach 2.4 cold flow. Results of the cold-flow tests were repeatable and within 15% of the value of Cf estimated from simple theory. The first gage design incorporated a cantilever beam with semiconductor strain gages to sense the shear on the floating head. Cooling water was routed both internally and around the external housing in order to control the temperature of the strain gages. This first gage was installed and tested in a rocket-based-combined-cycle (RBCC) engine model operating in the scramjet mode. The free-jet facility provided a Mach 6.4 flow with P0 = 1350 psia (9310 kPa) and T0 = 2800 °R (1555 °K). Local wall temperatures were measured between 850 and 900 °R (472-500 °K). Output from the RBCC scramjet tests was reasonable and repeatable. A second skin friction gage was designed for and tested in a wind tunnel model of the Hyper-X flight vehicle scramjet engine. These unsuccessful tests revealed the need for a radically different skin friction gage design. The third and final skin friction gage was specifically developed to be installed on the Hyper-X flight vehicle. Rather than the cantilever beam and semiconductor strain gages, the third skin friction gage made use of a flexure ring and metal foil strain gages to sense the shear. The water-cooling and oil-fill used on the previous skin friction sensors were eliminated. It was qualified for flight through a rigorous series of environmental tests, including pressure, temperature, vibration, and heat flux tests. Finally, the third skin friction gage was tested in the Hyper-X Engine Model (HXEM), a full-scale-partial-width wind tunnel model of the flight vehicle engine. These tests were conducted at Mach 6.5 enthalpy with P0 = 555 psia (3827 kPa) and h0 = 900 Btu/lbm in a freejet facility. The successful testing in the wind tunnel scramjet model provided the final verification of the gage before installation in the flight vehicle engine. The development, testing, and results of all three skin friction gages are discussed.
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Miller, P. "An experimental study of sonic and supersonic nozzles and their application to high pressure ejectors for aircraft attitude control." Thesis, University of Bath, 1988. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.380891.

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A study has been conducted of reaction controls for VSTOL aircraft using thrust augmenting ejector techniques. Rapid mixing nozzles have been developed for high pressure ejectors. Mass flow increases for sonic nozzles of up to 50\ at x/D=8 were recorded, compared with plain circular nozzles. Their use was found to improve the thrust performance of a simple ejector by 9\, and larger increases are believed possible. Results from an ejector performance prediction model were successfully compared with experimental data. The use of rapid mixing nozzles in a practical ejector design has been assessed. It is predicted that a maximum thrust increment of 20\ ·could be achieved, compared with a simple fully expanded jet flow.
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Books on the topic "Supersonic flight"

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ill, Hadler Terry, Jobson Ron ill, and Roffe Michael ill, eds. Supersonic flight. London: F. Watts, 1988.

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Faster than sound: The story of supersonic flight. 2nd ed. Sparkford, U.K: Haynes, 2008.

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Bill, Gunston. Faster Than Sound: Story of Supersonic Flight. Sparkford, Somerset: P. Stephens, 1992.

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Brown, Eric Melrose. Miles M.52: Gateway to supersonic flight. Stroud: Spellmount/History Press, 2012.

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Reithmaier, L. W. Mach 1 and beyond: The illustrated guide to high-speed flight. New York: TAB Books, 1995.

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Anderson, Griffin Y. An outlook on hypersonic flight. New York: AIAA, 1987.

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Bill, Gunston. Faster than sound: The story of supersonic flight. Sparkford: P. Stephens, 1992.

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Saltzman, Edwin J. Selected examples of NACA/NASA supersonic flight research. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Researh Center, 1995.

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Klimov, V. T., ed. Pravda o sverkhzvukovykh passazhirskikh samoletakh. Moskva, Russia (Federation): Moskovskiĭ rabochiĭ, 2000.

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Beamont, Roland. Testing early jets: Compressibility and the supersonic era. Shrewsbury, Eng: Airlife, 1990.

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Book chapters on the topic "Supersonic flight"

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Wegener, Peter P. "Toward High Speed: Supersonic and Hypersonic Flight." In What Makes Airplanes Fly?, 145–66. New York, NY: Springer US, 1991. http://dx.doi.org/10.1007/978-1-4684-0403-6_10.

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Wegener, Peter P. "Toward High Speed: Supersonic and Hypersonic Flight." In What Makes Airplanes Fly?, 169–93. New York, NY: Springer New York, 1997. http://dx.doi.org/10.1007/978-1-4612-2254-5_10.

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Sforza, P. M. "Interaction of Wing Vortices and Plumes in Supersonic Flight." In IUTAM Symposium on Dynamics of Slender Vortices, 415–24. Dordrecht: Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5042-2_35.

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Gardner, A. D., K. Hannemann, A. Paull, and J. Steelant. "Ground testing of the HyShot supersonic combustion flight experiment in HEG." In Shock Waves, 329–34. Berlin, Heidelberg: Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/978-3-540-27009-6_47.

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"SUPERSONIC FLIGHT." In Becoming a Spacewalker, 21. Purdue University Press, 2014. http://dx.doi.org/10.2307/j.ctv15wxpxz.9.

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Davies, Rose G. "Introduction of Supersonic Flight." In Aerodynamics Principles for Air Transport Pilots, 213–30. CRC Press, 2020. http://dx.doi.org/10.1201/9780429261152-11.

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"Transonic and supersonic flight." In Aircraft Performance, 252–82. Cambridge University Press, 1992. http://dx.doi.org/10.1017/cbo9780511607134.012.

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"Transonic and Supersonic Flows." In Aerodynamic Principles of Flight Vehicles, 129–70. Reston ,VA: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/5.9781600869174.0129.0170.

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"High-Supersonic/Hypersonic Flows." In Aerodynamic Principles of Flight Vehicles, 221–78. Reston ,VA: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/5.9781600869174.0221.0278.

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"High Supersonic Flight Vehicles Structures." In Encyclopedia of Thermal Stresses, 2226. Dordrecht: Springer Netherlands, 2014. http://dx.doi.org/10.1007/978-94-007-2739-7_100319.

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Conference papers on the topic "Supersonic flight"

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Vinh, Nguyen, and Yih-Feng Tzeng. "Optimum supersonic climb." In 19th Atmospheric Flight Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-3469.

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VINH, NGUYEN, and YIH-FENG TZENG. "Optimum poststall turning and supersonic turning." In Flight Simulation and Technologies. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-3659.

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Lapygin, V. I., T. V. Sazonova, and G. E. Yakunina. "On optimal configurations in supersonic flow." In Progress in Flight Physics, edited by P. Reijasse, D. Knight, M. Ivanov, and I. Lipatov. Les Ulis, France: EDP Sciences, 2013. http://dx.doi.org/10.1051/eucass/201305571.

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Schouten, Gerrit, and Peter Bakker. "Supersonic flight without downward shockwave." In 6th Aeroacoustics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-2018.

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DEVAN, LEROY. "Inviscid, nonaxisymmetric body, supersonic aerodynamic prediction." In 14th Atmospheric Flight Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2296.

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MASON, W., and JAEWOO LEE. "On optimal supersonic/hypersonic bodies." In Flight Simulation Technologies Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-3072.

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Blood, Eric, Mark Ivanov, Clara O'Farrell, Jason Ginn, Prasad Kutty, Chris Karlgaard, and Soumyo Dutta. "LDSD supersonic Flight Dynamics Test 1: Post-flight reconstruction." In 2015 IEEE Aerospace Conference. IEEE, 2015. http://dx.doi.org/10.1109/aero.2015.7119246.

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WARDLAW, JR., A., F. BALTAKIS, F. MARTIN, F. PRIOLO, and R. JETTMAR. "Godunov's method for supersonic tactical missile computations." In 12th Atmospheric Flight Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-1812.

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Mosbarger, Neal, and Paul King. "Time-dependent supersonic separation of tangent bodies." In 20th Atmospheric Flight Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-3462.

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Kulfan, Brenda. "Reynolds Numbers Considerations for Supersonic Flight." In 32nd AIAA Fluid Dynamics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-2839.

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Reports on the topic "Supersonic flight"

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Sahu, Jubaraj. Unsteady Flow Computations of a Finned Body in Supersonic Flight. Fort Belvoir, VA: Defense Technical Information Center, August 2007. http://dx.doi.org/10.21236/ada471736.

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DeSpirito, James. CFD Prediction of Magnus Effect in Subsonic to Supersonic Flight. Fort Belvoir, VA: Defense Technical Information Center, September 2009. http://dx.doi.org/10.21236/ada508090.

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Weinacht, Paul. A Direct-Fire Trajectory Model for Supersonic, Transonic, and Subsonic Projectile Flight. Fort Belvoir, VA: Defense Technical Information Center, July 2014. http://dx.doi.org/10.21236/ada607593.

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AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA. Volume 1. Performance Flight Testing. Annex 6A. Programmed Text for Supersonic Aerodynamics. Fort Belvoir, VA: Defense Technical Information Center, January 1991. http://dx.doi.org/10.21236/ada320218.

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

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Garrelick, Joel, Kyle Martini, Ron Brown, and J. M. Downing. An Evaluation of Structural Damage (Window Breakage) Potential in Callente, NV Under Current Supersonic Flight Restrictions at Nellis AFB. Fort Belvoir, VA: Defense Technical Information Center, January 1997. http://dx.doi.org/10.21236/ada329470.

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