Relevant bibliographies by topics / Hypersonic

Academic literature on the topic 'Hypersonic'

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Published: 4 June 2021
Last updated: 7 July 2024

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Journal articles on the topic "Hypersonic"

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Tuttle, S. L. "An Experiment for Teaching Hypersonic Aerodynamics to Undergraduate Mechanical Engineering Students." International Journal of Mechanical Engineering Education 28, no. 2 (April 2000): 151–62. http://dx.doi.org/10.7227/ijmee.28.2.4.

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An experiment designed to enhance the teaching of hypersonics to undergraduate mechanical engineering students is described. A small shock tunnel is used to demonstrate principles learned in the classroom. The pressures measured on two models at hypersonic Mach numbers are compared with suitable theoretical estimates. Typical results are shown and the success and relevance of the experiment is reported. Consideration is given to the teaching of such a highly specialized subject as hypersonic aerodynamics at the undergraduate level.
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de Araujo Martos, João Felipe, Israel da Silveira Rêgo, Sergio Nicholas Pachon Laiton, Bruno Coelho Lima, Felipe Jean Costa, and Paulo Gilberto de Paula Toro. "Experimental Investigation of Brazilian 14-X B Hypersonic Scramjet Aerospace Vehicle." International Journal of Aerospace Engineering 2017 (2017): 1–10. http://dx.doi.org/10.1155/2017/5496527.

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The Brazilian hypersonic scramjet aerospace vehicle 14-X B is a technological demonstrator of a hypersonic airbreathing propulsion system based on the supersonic combustion (scramjet) to be tested in flight into the Earth’s atmosphere at an altitude of 30 km and Mach number 7. The 14-X B has been designed at the Prof. Henry T. Nagamatsu Laboratory of Aerothermodynamics and Hypersonics, Institute for Advanced Studies (IEAv), Brazil. The IEAv T3 Hypersonic Shock Tunnel is a ground-test facility able to produce high Mach number and high enthalpy flows in the test section close to those encountered during the flight of the 14-X B into the Earth’s atmosphere at hypersonic flight speeds. A 1 m long stainless steel 14-X B model was experimentally investigated at T3 Hypersonic Shock Tunnel, for freestream Mach numbers ranging from 7 to 8. Static pressure measurements along the lower surface of the 14-X B, as well as high-speed Schlieren photographs taken from the 5.5° leading edge and the 14.5° deflection compression ramp, provided experimental data. Experimental data was compared to the analytical theoretical solutions and the computational fluid dynamics (CFD) simulations, showing good qualitative agreement and in consequence demonstrating the importance of these methods in the project of the 14-X B hypersonic scramjet aerospace vehicle.
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Seguin, Jory, Song Gao, Wagdi George Habashi, Dario Isola, and Guido Baruzzi. "A finite element solver for hypersonic flows in thermo-chemical non-equilibrium, Part I." International Journal of Numerical Methods for Heat & Fluid Flow 29, no. 7 (July 1, 2019): 2352–88. http://dx.doi.org/10.1108/hff-09-2018-0498.

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Purpose This paper aims to describe the physical and numerical modeling of a new computational fluid dynamics solver for hypersonic flows in thermo-chemical non-equilibrium. The code uses a blend of numerical techniques to ensure accuracy and robustness and to provide scalability for advanced hypersonic physics and complex three-dimensional (3D) flows. Design/methodology/approach The solver is based on an edge-based stabilized finite element method (FEM). The chemical and thermal non-equilibrium systems are loosely-coupled to provide flexibility and ease of implementation. Chemical non-equilibrium is modeled using a laminar finite-rate chemical kinetics model while a two-temperature model is used to account for thermodynamic non-equilibrium. The systems are solved implicitly in time to relax numerical stiffness. Investigations are performed on various canonical hypersonic geometries in two-dimensional and 3D. Findings The comparisons with numerical and experimental results demonstrate the suitability of the code for hypersonic non-equilibrium flows. Although convergence is shown to suffer to some extent from the loosely-coupled implementation, trading a fully-coupled system for a number of smaller ones improves computational time. Furthermore, the specialized numerical discretization offers a great deal of flexibility in the implementation of numerical flux functions and boundary conditions. Originality/value The FEM is often disregarded in hypersonics. This paper demonstrates that this method can be used successfully for these types of flows. The present findings will be built upon in a later paper to demonstrate the powerful numerical ability of this type of solver, particularly with respect to robustness on highly stretched unstructured anisotropic grids.
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Pletzer, Johannes, Didier Hauglustaine, Yann Cohen, Patrick Jöckel, and Volker Grewe. "The climate impact of hydrogen-powered hypersonic transport." Atmospheric Chemistry and Physics 22, no. 21 (November 8, 2022): 14323–54. http://dx.doi.org/10.5194/acp-22-14323-2022.

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Abstract. Hypersonic aircraft flying at Mach 5 to 8 are a means for traveling very long distances in extremely short times and are even significantly faster than supersonic transport (Mach 1.5 to 2.5). Fueled with liquid hydrogen (LH2), their emissions consist of water vapor (H2O), nitrogen oxides (NOx), and unburned hydrogen. If LH2 is produced in a climate- and carbon-neutral manner, carbon dioxide does not have to be included when calculating the climate footprint. H2O that is emitted near the surface has a very short residence time (hours) and thereby no considerable climate impact. Super- and hypersonic aviation emit at very high altitudes (15 to 35 km), and H2O residence times increase with altitude from months to several years, with large latitudinal variations. Therefore, emitted H2O has a substantial impact on climate via high altitude H2O changes. Since the (photo-)chemical lifetime of H2O largely decreases at altitudes above 30 km via the reaction with O(1D) and via photolysis, the question is whether the H2O climate impact from hypersonics flying above 30 km becomes smaller with higher cruise altitude. Here, we use two state-of-the-art chemistry–climate models and a climate response model to investigate atmospheric changes and respective climate impacts as a result of two potential hypersonic fleets flying at 26 and 35 km, respectively. We show, for the first time, that the (photo-)chemical H2O depletion of H2O emissions at these altitudes is overcompensated by a recombination of hydroxyl radicals to H2O and an enhanced methane and nitric acid depletion. These processes lead to an increase in H2O concentrations compared to a case with no emissions from hypersonic aircraft. This results in a steady increase with altitude of the H2O perturbation lifetime of up to 4.4±0.2 years at 35 km. We find a 18.2±2.8 and 36.9±3.4 mW m−2 increase in stratosphere-adjusted radiative forcing due to the two hypersonic fleets flying at 26 and 35 km, respectively. On average, ozone changes contribute 8 %–22 %, and water vapor changes contribute 78 %–92 % to the warming. Our calculations show that the climate impact, i.e., mean surface temperature change derived from the stratosphere-adjusted radiative forcing, of hypersonic transport is estimated to be roughly 8–20 times larger than a subsonic reference aircraft with the same transport volume (revenue passenger kilometers) and that the main contribution stems from H2O.
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Fan, Y., J. Chang, W. Bao, and D. Yu. "Effects of boundary-layer bleeding on unstart oscillatory flow of hypersonic inlets." Aeronautical Journal 114, no. 1157 (July 2010): 445–50. http://dx.doi.org/10.1017/s0001924000003924.

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Abstract The unsteady flowfield of a series of mixed-compression hypersonic inlets with different bleeding rates were numerically simulated. Firstly unstart oscillatory flow of hypersonic inlets caused by downstream massflow choking was discussed. Then the effects of boundary layer bleeding on the averaged performance parameter of hypersonic inlets, and on the dominant amplitude and frequency of unstart oscillatory flow of hypersonic inlets were presented. The reasons why the boundary-layer bleeding can suppress unstart oscillatory flow of hypersonic inlets were analysed. In conclusion, the averaged performance parameter of hypersonic inlets during a big buzz is improved greatly, and the dominant frequency of unstart oscillatory flow of hypersonic inlets is reduced in contrast with no bleeding, and all these are benefit to the design and operation of hypersonic inlets.
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Chang, J., D. Yu, W. Bao, Y. Fan, and Y. Shen. "Effects of boundary-layers bleeding on unstart/restart characteristics of hypersonic inlets." Aeronautical Journal 113, no. 1143 (May 2009): 319–27. http://dx.doi.org/10.1017/s0001924000002992.

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Abstract A series of mixed-compression hypersonic inlets at different bleeding rates were simulated at different freestream conditions in this paper. The unstart/restart characteristics of hypersonic inlets were analysed and the reasons why the unstart/restart phenomenon is in existence is presented. The unstart/restart characteristics of hypersonic inlets at different bleeding rates were given. The effects of boundary-layer bleeding on the performance parameter (mass-captured coefficient, total-pressure recovery coefficient), starting and restarting Mach number of hypersonic inlets were discussed. In conclusion, boundary-layer bleeding can improve the performance parameter of hypersonic inlets, and can reduce the starting and restarting Mach number, and can broad the operation range of the hypersonic inlet.
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Haley, J. G., T. P. McCall, I. W. Maynard, and B. Chudoba. "A sizing-based approach to evaluate hypersonic demonstrators: demonstrator-carrier constraints." Aeronautical Journal 124, no. 1279 (April 17, 2020): 1318–49. http://dx.doi.org/10.1017/aer.2020.30.

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ABSTRACTThe objective of this study is to identify, evaluate, and provide recommendations towards the realisation of near-term hypersonic flight hardware through the consideration of carrier vehicle constraints. The current rush of available funds for hypersonic research cannot cause a program to ignore growth potential for future missions. The prior NB-52 carrier vehicles, famous for the X-15 and X-43A missions, are retired. Next generation hypersonic demonstrator requirements will necessitate a substitution of carrier vehicle capability. Flight vehicle configuration, technology requirements, and recommendations are arrived at by constructing and evaluating a hypersonic technology demonstrator design matrix. This multi-disciplinary parametric sizing investigation of hypersonic vehicle demonstrators focuses on the evaluation of the combined carrier platform, booster, and hypersonic cruiser solution space topography. Promising baseline configurations are evaluated against operational requirements by trading fuel type, endurance cruise time, and payload weight. The multi-disciplinary study results are constrained with carrier payload mass and geometry limitations. The multi-disciplinary results provide physical insights into near-term hypersonic demonstrator payload and cruise time requirements that will stretch the capability of existing carrier aircraft. Any growth in hypersonic research aircraft size or capability will require new carrier vehicle investments.
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Chekov, A., and S. Babkina. "Hypersonic Weapons: Evolution or Revolution?" International Trends / Mezhdunarodnye protsessy 21, no. 2 (December 7, 2023): 83–102. http://dx.doi.org/10.17994/it.2023.21.2.73.5.

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Hypersonic strike systems have become a driving force in the development of offensive weapons. Academic literature offers two perspectives on the prospects of their impact on the military-strategic situation. One approach tends to position hypersonic weapons as a revolutionary technology, while the other proceeds from the premise that hypersonic strike systems represent an evolutionary development of offensive systems. The objective of this article is to establish the specifics and limits of the hypersonic weapons impact on the existing military-strategic balance. The paper analyzes the problem of hypersonic weapons classification, their role and place in military strategy, as well as the evolution and prospects of the Russian, U.S. and Chinese programs on hypersonic weapons. The authors conclude that the advantages of hypersonic weapons cannot automatically be transformed into a guaranteed success amid a full-scale military conflict and are largely available to other strike systems based on less advanced technological solutions. The key scenario, where the benefits of hypersonic weapons can be realized the most, is a limited conflict, in which they are used for the surprise defeat of highly-protected priority targets and the establishment of theater domination. This is evidenced by the hypersonic development programs of the leading military powers – Russia, the United States, and China, – each of which is more or less committed to developing medium- and short-range systems. The implications of the unfolding hypersonic arms race for strategic stability are ambiguous. On the one hand, forward deployment of such systems increases the risks of escalation; reduced flight time to enemy strategic infrastructure facilities encourages the adversary to adopt more aggressive retaliation postures based on the principle of launch-on-warning rather than post-attack. On the other hand, the possession of hypersonic weapons by both sides in the same theater increases their mutual vulnerability and can thus play a stabilizing role.
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LEES, LESTER. "Hypersonic Flow." Journal of Spacecraft and Rockets 40, no. 5 (September 2003): 700–735. http://dx.doi.org/10.2514/2.6897.

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Cheng, Sin-I. "Hypersonic propulsion." Progress in Energy and Combustion Science 15, no. 3 (January 1989): 183–202. http://dx.doi.org/10.1016/0360-1285(89)90008-7.

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Dissertations / Theses on the topic "Hypersonic"

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Kumar, D. "Hypersonic control effectiveness." Thesis, Cranfield University, 1995. http://hdl.handle.net/1826/4252.

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The present study analyses the effects of a number of geometric parameters on the performance of a trailing edge control flap on a hypersonic body. The tests were conducted in a gun tunnel at Mach 8.2 and Mach 12.3. The study revealed that flap deflection promoted separation lengthscales and boundary layer transition. The latter significantly increased the local aerothermal loads on the flap. For well separated flows, flap heat transfer rates were successfully predicted by reference temperature theory. The promotion of transition caused a progressive reduction in the lengthscales of separated flows. In a free-flight environment, vehicle incidence varies considerably. Incidence was found to promote transition on both flat plates and control flaps. The latter resulted in a considerable increase in flap heat transfer. A modified version of reference temperature theory successfully predicted the aerothermal loads on the flap. For laminar and transitional interactions, the separated flow lengthscale was found to have a complex variation with incidence. A number of relevant flow parameters were identified. The intense heat loads on a vehicle in hypersonic flight dictates the blunting of the leading edge. This strengthens the leading edge shock structure and generates an entropy layer. Bluntness was found to significantly decrease the separation interaction scales on the flap. This was due to a reduction in the pressure recovered on the flap. The latter adverse affects control effectiveness. The aerothermal loads on the control flap was successfully predicted by reference temperature theory. An investigation into the efficiency of an under-expanded transverse jet controls was conducted on an axi-symmetric slender blunt cone. Force measurements found that the interaction augmented the jet reaction force by 70% at zero incidence. This increased to 110% at low incidence. The experiments found that the scale of the interaction region was determined by Poj/pes. Using this parameter, a closed loop algorithm for the shape of the separation front was developed. The latter can be used to predict jet reaction control effectiveness.
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Netterfield, Michael Phillip. "Hypersonic cavity flows." Thesis, Imperial College London, 1989. http://hdl.handle.net/10044/1/47586.

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Gorishnyy, Taras. "Hypersonic phononic crystals." Thesis, Massachusetts Institute of Technology, 2007. http://hdl.handle.net/1721.1/42133.

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Thesis (Ph. D.)--Massachusetts Institute of Technology, Dept. of Materials Science and Engineering, 2007.
Includes bibliographical references (p. 133-140).
Manipulation of the distribution of phonons inM a solid is important for both basic science and applications ranging from heat management to reduction of noise in electronic circuits and creating materials with superior acoustic and acousto-optical properties. This thesis explores hypersonic phononic crystals as means to achieve control over high frequency acoustic phonons. An integrated approach to fabrication, measurement and analysis of hypersonic phononic crystals with band gaps in the GHz range is presented. First, the phonon dispersion relation for one dimensional polymeric phononic crystals fabricated by coextrusion of a large number of poly(methylmethacrylate)/poly(carbonate) and poly(methylmethacrylate)/poly(ethylene terephthalate) bilayer pairs is investigated as a function of a lattice constant and composition using Brillouin light scattering and numerical simulations. This set of relatively simple multilayer structures represents an excellent platform to gain a basic understanding of phononic band gap phenomena. In addition, their in-plane phonon dispersion is used to extract information about the elastic constants and glass transition temperatures of individual nanolayers in a periodic multilayer arrangement. Next, two dimensional epoxy/air phononic crystals fabricated in a photoresist using interference lithography are studied. These structures are 2D single crystalline, enabling direction-resolved measurements of their phonon dispersion relation. As a result, the complete experimental phononic band diagram is obtained and correlated with numerical simulations. Finally, phononic properties of three dimensional elastomeric poly(dimethylsiloxane) crystals are investigated and the mechanical tunability of their dispersion relation is demonstrated.
(cont.) This set of structures forms the basis for understanding how to design and fabricate acoustic and acousto-optical devices with performance characteristics that can be adjusted dynamically during operation. The investigations described in this thesis demonstrate both theoretically and experimentally that 1D, 2D and 3D periodic submicron structures have complex phonon dispersion relations at GHz frequencies. As a result, these crystals can be used to manipulate the flow of random thermal phonons as well as externally generated acoustic waves resulting in novel acoustic and thermal properties.
by Taras Gorishnyy.
Ph.D.
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Haq, Z. U. "Hypersonic vehicle interference heating." Thesis, University of Southampton, 1993. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.336171.

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Sagerman, Denton Gregory. "Hypersonic Experimental Aero-thermal Capability Study Through Multilevel Fidelity Computational Fluid Dynamics." University of Dayton / OhioLINK, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1499433256220438.

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Gibson, Travis Eli. "Adaptive control of hypersonic vehicles." Thesis, Massachusetts Institute of Technology, 2008. http://hdl.handle.net/1721.1/46635.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 2008.
Includes bibliographical references (p. 105-109).
The guidance, navigation and control of hypersonic vehicles are highly challenging tasks due to the fact that the dynamics of the airframe, propulsion system and structure are integrated and highly interactive. Such a coupling makes it difficult to model various components with a requisite degree of accuracy. This in turn makes various control tasks including altitude and velocity command tracking in the cruise phase of the flight extremely difficult. This work proposes an adaptive controller for a hypersonic cruise vehicle subject to: aerodynamic uncertainties, center-of-gravity movements, actuator saturation, failures, and time-delays. The adaptive control architecture is based on a linearized model of the underlying rigid body dynamics and explicitly accommodates for all uncertainties. Within the control structure is a baseline Proportional Integral Filter commonly used in optimal control designs. The control design is validated using a highfidelity HSV model that incorporates various effects including coupling between structural modes and aerodynamics, and thrust pitch coupling. Analysis of the Adaptive Robust Controller for Hypersonic Vehicles (ARCH) is carried out using a control verification methodology. This methodology illustrates the resilience of the controller to the uncertainties mentioned above for a set of closed-loop requirements that prevent excessive structural loading, poor tracking performance, and engine stalls. This analysis enables the quantification of the improvements that result from using and adaptive controller for a typical maneuver in the V-h space under cruise conditions.
by Travis Eli Gibson.
S.M.
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Starkey, Ryan P., Mark J. Lewis, and Charles H. Jones. "PLASMA TELEMETRY IN HYPERSONIC FLIGHT." International Foundation for Telemetering, 2002. http://hdl.handle.net/10150/607506.

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International Telemetering Conference Proceedings / October 21, 2002 / Town & Country Hotel and Conference Center, San Diego, California
Problems associated with telemetry blackout caused by the plasma sheath surrounding a hypersonic vehicle are addressed. In particular, the critical nature of overcoming this limitation for test and evaluation purposes is detailed. Since the telemetry blackout causes great concern for atmospheric cruise vehicles, ballistic missiles, and reentry vehicles, there have been many proposed approaches to solving the problem. This paper overviews aerodynamic design methodologies, for which the required technologies are only now being realized, which may allow for uninterrupted transmission through a plasma sheath. The severity of the signal attenuation is dependent on vehicle configuration, trajectory, flightpath, and mission.
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Ajmani, Kumud. "Turbulence modeling in hypersonic inlets." Thesis, Virginia Polytechnic Institute and State University, 1987. http://hdl.handle.net/10919/101365.

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A study is conducted to analyze the performance of different turbulence models when applied to flow through a Mach 7.4 hypersonic inlet. The analysis, which is two-dimensional, is done by comparing computational results from a Parabolized Navier Stokes code, with experimental data. The McDonald Camarata (MC) and Baldwin Lomax (BL) models were the two zero-equation models used in the study. The Turbulent Kinetic Energy (TKE) model was chosen as a representative higher order model. The MC model, when run with transition of flow, provides a solution which compares excellently with the data. Transition has a first order effect on the overall solution provided by the code. The BL model predicts separation of flow in the inlet, which contradicts experimental findings. The TKE model does not perform any better than the MC and BL models, despite the fact that it is a higher order turbulence model. The BL and TKE models predict transition in the inlet at a location which is much earlier than observed in the experiment. This may be attributed to the empirical constants used to determine the point of transition.
M.S.
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Laurence, Stuart Jon Hornung H. G. "Proximal bodies in hypersonic flow /." Diss., Pasadena, Calif. : Caltech, 2006. http://resolver.caltech.edu/CaltechETD:etd-04242006-172719.

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Louie, Ken. "Mathematical problems in inviscid hypersonic flow." Thesis, University of Oxford, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.291297.

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Books on the topic "Hypersonic"

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Hypersonic flow. New York: Wiley, 1994.

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HEPPENHEIMER, T. A. Hypersonic technologies. Arlington, Va: Pasha Publications, 1993.

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Hypersonic aerothermodynamics. Washington, DC: American Institute of Aeronautics and Astronautics, 1994.

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Park, Chul. Nonequilibrium hypersonic aerothermodynamics. New York: Wiley, 1990.

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T, Pratt David, ed. Hypersonic airbreathing propulsion. Washington, D.C: American Institute of Aeronautics and Astronautics, 1994.

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Griffith, Wayland C. Hypersonic nozzle design. Raleigh, N. C: North Carolina State University, 1989.

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Hani, Alkamhawi, and United States. National Aeronautics and Space Administration., eds. Hypersonic aircraft design. [Columbus, Ohio]: Ohio State University, 1990.

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Bruno, Claudio. Airbreathing Hypersonic Propulsion. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-7927-9.

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L, Rausch Vincent, and United States. National Aeronautics and Space Administration., eds. Airbreathing hypersonic systems focus at NASA Langley Research Center. Washington, DC: American Institute of Aeronautics and Astronautics, 1998.

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N, Pessin David, and Ames Research Center, eds. Aerodynamic analysis of hypersonic waverider aircraft. San Luis Obispo, CA: Cal Poly State University, 1993.

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Book chapters on the topic "Hypersonic"

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Weik, Martin H. "hypersonic." In Computer Science and Communications Dictionary, 742. Boston, MA: Springer US, 2000. http://dx.doi.org/10.1007/1-4020-0613-6_8548.

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Lele, Ajey. "Hypersonic Weapons." In Disruptive Technologies for the Militaries and Security, 47–78. Singapore: Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-13-3384-2_3.

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Gülçat, Ülgen. "Hypersonic Flow." In Fundamentals of Modern Unsteady Aerodynamics, 205–58. Singapore: Springer Singapore, 2015. http://dx.doi.org/10.1007/978-981-10-0018-8_7.

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Anderson, John D. "Hypersonic Flow." In Handbook of Fluid Dynamics and Fluid Machinery, 629–70. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2007. http://dx.doi.org/10.1002/9780470172636.ch10.

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GÜlçat, Ülgen. "Hypersonic Flow." In Fundamentals of Modern Unsteady Aerodynamics, 209–64. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-60777-7_7.

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Kaushik, Mrinal. "Hypersonic Flows." In Theoretical and Experimental Aerodynamics, 237–50. Singapore: Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-13-1678-4_10.

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Wu, Mingxi. "Hypersonic Confrontation." In Intelligent Warfare, 282–98. London: Routledge, 2022. http://dx.doi.org/10.4324/b22974-12.

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Gülçat, Ülgen. "Hypersonic Flow." In Fundamentals of Modern Unsteady Aerodynamics, 193–244. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-14761-6_7.

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Bruno, Claudio. "Why Hypersonic Propulsion?" In Airbreathing Hypersonic Propulsion, 1–17. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-7927-9_1.

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Bruno, Claudio. "Hypersonic Flow Simulation." In Airbreathing Hypersonic Propulsion, 247–68. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-7927-9_7.

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Conference papers on the topic "Hypersonic"

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HAMM, DAVE, and DANA BEST. "Hypersonic design." In AlAA 4th International Aerospace Planes Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-5077.

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Kocian, Travis S., Alexander Moyes, Helen L. Reed, Stuart A. Craig, William S. Saric, Steven P. Schneider, and Josh Edelman. "Hypersonic Crossflow Instability." In 2018 AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-0061.

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SPEER, T., and A. HOYT. "European hypersonic technology." In 15th Aerodynamic Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-1993.

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Youssef, Hussein, Rajiv Chowdhry, Howard Lee, and Patrick Rodi. "Hypersonic Skipping Trajectory." In AIAA Guidance, Navigation, and Control Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-5498.

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NAGAMATSU, H., and R. SHEER, JR. "Hypersonic gas dynamics." In 20th Thermophysics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-999.

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WILLIAMSON, W. "Hypersonic flight testing." In 17th Aerospace Ground Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-3989.

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Nieto, Andy, Karen Perez, Marcus Rojas, Omar Rodriguez, Oscar Fernandez, Skyler Salman, and Gecheng Zha. "Towards High Efficiency Hypersonic Flight-Hypersonic Bi- Directional Flying Wing." In 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-398.

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Candler, G., I. Nompelis, M. C. Druguet, M. Holden, T. Wadhams, I. Boyd, and W. L. Wang. "CFD validation for hypersonic flight - Hypersonic double-cone flow simulations." In 40th AIAA Aerospace Sciences Meeting & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-581.

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Melville, Maelyn, and Dennis Helmich. "Hypersonic Weapons Summit: Promoting Leadership in Hypersonic Development Among Research Institutions." In Proposed for presentation at the Hypersonic Weapons Summit 2021 held September 28-30, 2021 in Virtual,. US DOE, 2021. http://dx.doi.org/10.2172/1890378.

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Thuruthimattam, B. J., P. P. Friedmann, J. J. McNamara, and K. G. Powell. "Modeling Approaches to Hypersonic Aeroelasticity." In ASME 2002 International Mechanical Engineering Congress and Exposition. ASMEDC, 2002. http://dx.doi.org/10.1115/imece2002-32943.

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The hypersonic aeroelastic problem of a double wedge airfoil typical cross-section is studied using three different unsteady aerodynamic loads: (1) third order piston theory, (2) Euler solution, and (3) unsteady Navier-Stokes aerodynamics. Computational aeroelastic response results are obtained, and compared with piston theory solutions for a variety of flight conditions. Aeroelastic behavior is studied for 7 < M < 15 at an altitude of 70,000 feet. A parametric study of offsets and wedge angles is conducted. Piston theory and Euler solutions are fairly close below the flutter boundary, and differences increase with increase in Mach number, close to the flutter boundary. Differences between viscous and inviscid aeroelastic behavior can be substantial. The results presented serve as a partial validation of the CFL3D code for the hypersonic flight regime.
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Reports on the topic "Hypersonic"

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Noone, Emily, and Lydia Harriss. Hypersonic missiles. Parliamentary Office of Science and Technology, June 2023. http://dx.doi.org/10.58248/pn696.

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This POSTnote looks at hypersonic missile technologies, efforts to develop them, potential applications, and the possible challenges they may present for missile defence and global stability. Key Points: • Hypersonic missiles combine speeds of over five times the speed of sound with significant manoeuvrability during flight. • Their manoeuvrability enables them to change trajectory during flight, making their flight-path and target difficult to predict. • They fly at lower altitudes than ballistic missiles, which means that they may be harder to track at long distances with some surface-based sensors, such as certain radar. • There are two main types of hypersonic missile: hypersonic glide vehicles (HGVs) and hypersonic cruise missiles (HCMs). • HGVs are mounted onto rocket boosters for launch and may be accelerated to speeds of Mach 20 or more. The glider then separates from the booster and flies unpowered in the Earth’s upper atmosphere at altitudes of 30-80 km, before diving towards the target. • HCMs typically have a ramjet or scramjet engine that enables them to reach hypersonic speeds at altitudes of 20-40 km. • China and Russia have reportedly deployed hypersonic missiles that could deliver conventional or nuclear weapons. The US is testing multiple hypersonic technologies. • The AUKUS agreement between the UK, US and Australia includes developing hyper-sonic and counter-hypersonic technologies. • Developing hypersonic missiles requires significant research and development challenges to be overcome, contributing to their high development and manufacturing costs. • The speed, manoeuvrability and altitude of hypersonic missiles may challenge existing missile defences, although their uses and effectiveness are still being assessed. • Defence analysts disagree about the potential implications of hypersonic missiles for global peace and stability. Some suggest they could increase the risk of conflict escalation, while others say that they will not alter the strategic balance between nuclear powers. • Arms control, export controls and other measures may help limit potential harm to peace and stability, but these approaches face challenges.
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Brockmann, Kolja, and Dmitry Stefanovich. Hypersonic Boost-Glide Systems and Hypersonic Cruise Missiles: Challenges for the Missile Technology Control Regime. Stockholm International Peace Research Institute, April 2022. http://dx.doi.org/10.55163/bdyx5243.

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An increasing number of states are pursuing hypersonic missile development programmes, including for hypersonic boost-glide systems and hypersonic cruise missiles. Hypersonic missiles combine hypersonic speed and manoeuvrability which can result in target ambiguity, render missile defences ineffective and reduce warning times. Some hypersonic missiles are developed as delivery systems both for nuclear and conventional payloads. The combination of these capabilities may have escalatory or destabilizing effects. The Missile Technology Control Regime (MTCR) is the main instrument through which states seek to harmonize export control policies to govern the transfer of missile technology. It is key to ensure that the MTCR’s guidelines and control list adequately cover hypersonic missiles and related goods and technologies. This paper seeks to improve the understanding of hypersonic missiles, increase awareness among policy makers and export control officials, and inform the ongoing technical and policy discussions within the MTCR to strengthen efforts to limit the proliferation of hypersonic missiles.
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Levermore, C. D., and Moysey Brio. Hypersonic Fluid Dynamics. Fort Belvoir, VA: Defense Technical Information Center, November 1994. http://dx.doi.org/10.21236/ada295493.

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Anderson, Jr, and John D. Hypersonic Aerodynamics Fellowships. Fort Belvoir, VA: Defense Technical Information Center, February 1991. http://dx.doi.org/10.21236/ada233584.

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Grossir, Guillaume. On the design of quiet hypersonic wind tunnels. Von Karman Institute for Fluid Dynamics, December 2020. http://dx.doi.org/10.35294/tm57.

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This document presents a thorough literature review on the development of hypersonic quiet tunnels. The concept of boundary layer transition in high-speed flows is presented first. Its consequences on the free-stream turbulence levels in ground facilities are reviewed next, demonstrating that running boundary layers along the nozzle walls must remain laminar for quiet operation. The design key points that enable laminar boundary layers and hypersonic operation with low free-stream noise levels are then identified and discussed. The few quiet facilities currently operating through the world are also presented, along with their design characteristics and performances. The expected characteristics and performances of a European quiet tunnel are also discussed, along with flow characterization methodologies and different measurement techniques. It is finally shown that the required expertise to establish the first European quiet hypersonic wind tunnel is mostly at hand.
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Anderson, John D., and Jr. Fellowships in Hypersonic Aerodynamics. Fort Belvoir, VA: Defense Technical Information Center, February 1988. http://dx.doi.org/10.21236/ada194265.

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Miles, Richard B., and Garry L. Brown. Radiatively Driven Hypersonic Wind Tunnel. Fort Belvoir, VA: Defense Technical Information Center, May 2002. http://dx.doi.org/10.21236/ada403037.

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Brown, Michael S., and Jeffrey M. Donbar. Diagnostics for Hypersonic Engine Control. Fort Belvoir, VA: Defense Technical Information Center, February 2015. http://dx.doi.org/10.21236/ada613800.

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Reshotko, Eli. Time-Dependent Hypersonic Viscous Interactions. Fort Belvoir, VA: Defense Technical Information Center, June 1987. http://dx.doi.org/10.21236/ada185764.

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Brown, Michael S., and Jeffrey M. Donbar. Diagnostics for Hypersonic Engine Control. Fort Belvoir, VA: Defense Technical Information Center, February 2013. http://dx.doi.org/10.21236/ada578570.

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