Relevant bibliographies by topics / Supersonic speed conditions

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

Academic literature on the topic 'Supersonic speed conditions'

Author: Grafiati
Published: 5 June 2025
Last updated: 2 August 2025

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Journal articles on the topic "Supersonic speed conditions"

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Aprovitola, Andrea, Oleksandr Dyblenko, Giuseppe Pezzella, and Antonio Viviani. "Aerodynamic Analysis of a Supersonic Transport Aircraft at Low and High Speed Flow Conditions." Aerospace 9, no. 8 (2022): 411. http://dx.doi.org/10.3390/aerospace9080411.

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The recent improvement of technology readiness level in aeronautics and the renewed demand for faster transportation are driving the rebirth of supersonic flight for commercial aviation. However, the design of a future supersonic aircraft is still very challenging due to the complexity of several problems, such as static stability performance during the acceleration phase from subsonic speeds to supersonic speeds. Additionally, the interest of scientific community in open source numerical platform as a valid tool for a reliable and affordable aerodynamic design is considerably growing. In this
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Ищенко, А. Н., В. В. Буркин, А. С. Дьячковский та ін. "Одиночное и совместное движение суперкавитирующих ударников в сверхзвуковом режиме в воде". Журнал технической физики 46, № 23 (2020): 22. http://dx.doi.org/10.21883/pjtf.2020.23.50343.18484.

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The research considers features of the underwater movement of single and two supercavitating strikers when simultaneous penetration into the water at speeds exceeding of sound speed. Conditions which provide non-destructive penetration into the water of strikers and their stable movement along an aiming trajectory at the transonic speed range has been developed. A stable cooperative movement of two strikers at the supersonic speed has been realized.
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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 (2008): 141–51. http://dx.doi.org/10.1017/s0001924000002074.

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Abstract The first generation of supersonic commercial transportation has seen three serious attempts to arrive at an economically and environmentally viable aircraft. The US B2707-200/300 design was cancelled early before a prototype could emerge; the Russian Tu-144 design succeeded to become the first supersonic transport but spanned only a few years of restricted airline service; the Anglo-French Concorde endured more than 27 glamorous airline service years until the last of its species was retired on 30 August 2003. This first generation was followed by a second generation of supersonic co
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Lou, Fangyuan, John Charles Fabian, and Nicole Leanne Key. "Interpreting Aerodynamics of a Transonic Impeller from Static Pressure Measurements." International Journal of Rotating Machinery 2018 (2018): 1–9. http://dx.doi.org/10.1155/2018/7281691.

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This paper investigates the aerodynamics of a transonic impeller using static pressure measurements. The impeller is a high-speed, high-pressure-ratio wheel used in small gas turbine engines. The experiment was conducted on the single stage centrifugal compressor facility in the compressor research laboratory at Purdue University. Data were acquired from choke to near-surge at four different corrected speeds (Nc) from 80% to 100% design speed, which covers both subsonic and supersonic inlet conditions. Details of the impeller flow field are discussed using data acquired from both steady and ti
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De Tavernier, Delphine, and Dominic von Terzi. "The emergence of supersonic flow on wind turbines." Journal of Physics: Conference Series 2265, no. 4 (2022): 042068. http://dx.doi.org/10.1088/1742-6596/2265/4/042068.

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Abstract The future generation of wind turbines will be characterised by longer and more flexible blades. These large wind turbines are facing higher Reynolds numbers, as a consequence of longer chord lengths and increased relative wind speeds. Higher tip speeds, however, also result in an increased Mach number. Although the maximum tip speed in steady design conditions may remain (well) below the critical value, the presence of turbulence, wind gusts, blade deflections, etc. in combination with the flow acceleration over the airfoil surface, may cause a significant increase in the velocity pe
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Aprovitola, Andrea, Pasquale Emanuele Di Nuzzo, Giuseppe Pezzella, and Antonio Viviani. "Aerodynamic Analysis of a Supersonic Transport Aircraft at Landing Speed Conditions." Energies 14, no. 20 (2021): 6615. http://dx.doi.org/10.3390/en14206615.

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Supersonic flight for commercial aviation is gaining a renewed interest, especially for business aviation, which demands the reduction of flight times for transcontinental routes. So far, the promise of civil supersonic flight has only been afforded by the Concorde and Tupolev T-144 aircraft. However, little or nothing can be found about the aerodynamics of these aeroshapes, the knowledge of which is extremely interesting to obtain before the development of the next-generation high-speed aircraft. Therefore, the present research effort aimed at filling in the lack of data on a Concorde-like ae
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Chai, Xiaochuan, Prahladh S. Iyer, and Krishnan Mahesh. "Numerical study of high speed jets in crossflow." Journal of Fluid Mechanics 785 (November 13, 2015): 152–88. http://dx.doi.org/10.1017/jfm.2015.612.

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Large-eddy simulation (LES) and dynamic mode decomposition (DMD) are used to study an underexpanded sonic jet injected into a supersonic crossflow and an overexpanded supersonic jet injected into a subsonic crossflow, where the flow conditions are based on the experiments of Santiago & Dutton (J. Propul. Power, vol. 13 (2), 1997, pp. 264–273) and Beresh et al. (AIAA J., vol. 43, 2005a, pp. 379–389), respectively. The simulations successfully reproduce experimentally observed shock systems and vortical structures. The time averaged flow fields are compared to the experimental results, and g
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Kanik Mittal and Sachin Srivastava. "SCRAMJET: Future High Speed Aircraft." Acceleron Aerospace Journal 3, no. 7 (2024): 785. https://doi.org/10.61359/11.2106-2476.

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In the current era of technological advancement, the scramjet has become one of the most conventional engines for achieving supersonic speeds in aircraft. The scramjet comprises three basic components: the inlet, combustor, and nozzle. Various fuels, such as Kerosene, JP-7, JP-8, hydrocarbon-based fuels, and hydrogen, have been used in scramjets, demonstrating distinct performance characteristics. Tests have shown that hydrocarbon-fueled scramjet engines can achieve a Mach number range of 3.5 to 7, while solid-fueled scramjets have the potential to achieve combustion efficiencies of 0.7–0.9. F
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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 (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.
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Xu, Xing, and Jun Hu. "Research on Aerodynamic Characteristics of Lateral Jet Control Technology." Advanced Materials Research 709 (June 2013): 253–56. http://dx.doi.org/10.4028/www.scientific.net/amr.709.253.

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This paper takes N-S equation as the basic control equation, selects turbulence model, and adopts the sliding mesh technology to conduct numerical simulation for the interference of missile jet flow and inflow on the flow field in different flow conditions. The results indicate that: the lift coefficient, drag coefficient and pressure center coefficient of missile body change with the changes of flowMach number and attack angle. The lift coefficient increases with the increase of Mach number in subsonic speed, decreases with the increase of Mach number in supersonic speed, and reaches a maximu
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Dissertations / Theses on the topic "Supersonic speed conditions"

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Wang, Peng C. "Large eddy simulation of high speed convergent-divergent nozzle flows." Thesis, Loughborough University, 2013. https://dspace.lboro.ac.uk/2134/11937.

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Interest in developing a detailed understanding of jet plume aerodynamics has increased significantly in recent years, for both civil (noise reduction) and military (Infra-Red signature modelling) aerospace applications. Such flows are critically dependent on turbulence modelling of the jet plume shear layer mixing. Reynolds averaged Navier Stokes (RANS) CFD tends to overpredict while Large Eddy Simulation (LES) CFD underpredicts potential core length. Difficulties in LES begin with the challenge of providing accurate resolution of thin turbulent boundary layers at nozzle exit. Providing physi
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Books on the topic "Supersonic speed conditions"

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

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Center, Langley Research, ed. Initial piloted simulation evaluation of the Reference-H High-Speed Civil Transport design during takeoff and recovery from limit flight conditions. National Aeronautics and Space Administration, Langley Research Center, 1999.

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Book chapters on the topic "Supersonic speed conditions"

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Zheltovodov, A. A., A. A. Pavlov, E. H. Shilein, and V. N. Yakovlev. "Interconnectionship Between the Flow Separation and the Direct and Inverse Transition at Supersonic Speed Conditions." In Laminar-Turbulent Transition. Springer Berlin Heidelberg, 1985. http://dx.doi.org/10.1007/978-3-642-82462-3_61.

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Borisov, A. V., A. A. Zheltovodov, V. M. Trofimov, E. Kh Shileyn, and V. N. Yakovlev. "Analysis of Turbulent Separated Flows in the Vicinity of Two-Dimensional Obstacles Under Supersonic Speeds Conditions." In Separated Flows and Jets. Springer Berlin Heidelberg, 1991. http://dx.doi.org/10.1007/978-3-642-84447-8_43.

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Sandeep, Juluru. "Design and Performance of Hypersonic Intake for Scramjet Engine." In Hypersonic and Supersonic Flight - Advances in Aerodynamics, Materials, and Vehicle Design [Working Title]. IntechOpen, 2022. http://dx.doi.org/10.5772/intechopen.107840.

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Rockets are the only vehicles to reach hypersonic speeds with non-airbreathing engines carrying both fuel and oxidizer increasing budget of space exploration. So, the desire to achieve hypersonic speeds at low cost has led to the development of air-breathing engines known as supersonic combustion ramjet engines or scramjet engines. The most complex part in the development of the scramjet engine is the intake. Free-stream hypersonic speed flow will be compressed in intake and processed into the combustor as per the required pressure and temperature. The high-pressurized flow can be provided to
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Verma, Kumari Ambe, K. M. Pandey, K. K. Sharma, and Dhiren R. Patel. "Review of the Role of Geometrical Modification of Scramjet Combustor on Performance Characteristics." In Materials and Technologies for a Green Environment. BENTHAM SCIENCE PUBLISHERS, 2023. http://dx.doi.org/10.2174/9789815051216123010007.

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The current scenario in the field of aviation is focused on hypersonic-speed vehicles. To achieve the required performance, engines have to be designed in such a way that their outcome should be maximum. Nowadays high-speed performance engines have utilized a type of air-breathing engine amongst which, the scramjet is found appropriate. However, the engine can only perform under atmospheric area because the supersonic combustion ramjet engine utilizes the atmospheric air as an oxidizer. Nonetheless, engines do not comprise any rotating or moving parts. So, to complete the mixing and chemical k
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Ardaneh, Fatemeh, Marta Zocca, Antti Uusitalo, and Teemu Turunen-Saaresti. "Numerical Analysis of Aerodynamics and Performance of a Radial-Inflow Micro-ORC Turbine." In Proceedings of the 7th International Seminar on ORC Power System (ORC 2023), 2024th ed. Editorial Universidad de Sevilla, 2024. http://dx.doi.org/10.12795/9788447227457_59.

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Organic Rankine Cycle (ORC) has proven to be an effective way to recover waste heat. The performance of ORC systems is profoundly affected by turbine selection, which is one of the most critical components. In this study, a numerical aerodynamic analysis of a micro-ORC turbine is carried out as an effort towards the formulation of a reduced order model (ROM) of the turbine for the dynamic simulation of the complete ORC system. The studied turbine is the radial-inflow turbine of the waste heat recovery micro-ORC test rig at the Laboratory of Fluid Dynamics, LUT University. The performance of th
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Qiu, Ju, and Chaofeng Liu. "Verification and Validation of Supersonic Flutter of Rudder Model for Experiment." In Optimization Problems in Engineering [Working Title]. IntechOpen, 2021. http://dx.doi.org/10.5772/intechopen.98384.

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The abrupt and explosive nature of flutter is a dangerous failure mode, which is closely related to the structural modes. In this work, the principal goal of the study is to produce the model, which is used very accurately for flutter predictions. Mode correctness of the model can correct the test deflects by the optimization technique----Sequential Quadratic Programming (SQP). The optimization of two finite element models for two flight conditions, transonic and supersonic speeds, had the different objectives which were defined by the nonlinear and linear eigenvector errors. The first and sec
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Wang, Xiyu, Yuanbo Xue, Fangyi Wu, Liyun Tao, Yongliang Tian, and Hu Liu. "A Conceptual Design of a Two-Class Retrievable Multipurpose Space Transporter." In Advances in Transdisciplinary Engineering. IOS Press, 2025. https://doi.org/10.3233/atde250348.

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For the requirements of future spacecraft including flexible launch base, long window period, multi-purpose, module reorganization, space-sky fusion, wide-domain operation, this paper designs a two-stage repeatable space transporter, with a payload of 10 tons. To meet the requirements of wide-domain flight, a power system and aerodynamic layout are designed for subsonic, transonic, supersonic, and hypersonic conditions. Additionally, the electromagnetic, aerodynamic, mechanical coupling guideway separation guide rail are developed along with corresponding flight control systems for the two cla
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Conference papers on the topic "Supersonic speed conditions"

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Magee, Todd E., Patrick J. Hayes, Andrew J. Dorgan, and Abdollah Khodadoust. "Dynamic Stability Characteristics for Commercial Supersonic Configurations at Low-Speed Flight Conditions." In AIAA SCITECH 2022 Forum. American Institute of Aeronautics and Astronautics, 2022. http://dx.doi.org/10.2514/6.2022-1802.

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Magee, Todd E., Patrick J. Hayes, and Abdollah Khodadoust. "Dynamic Stability Characteristics for Commercial Supersonic Configurations at Low-Speed Flight Conditions – Part II." In AIAA SCITECH 2024 Forum. American Institute of Aeronautics and Astronautics, 2024. http://dx.doi.org/10.2514/6.2024-0900.

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Magee, Todd E., Patrick J. Hayes, and Abdollah Khodadoust. "Dynamic Stability Characteristics for Commercial Supersonic Configurations at Low-Speed Flight Conditions – Part III." In AIAA SCITECH 2025 Forum. American Institute of Aeronautics and Astronautics, 2025. https://doi.org/10.2514/6.2025-2363.

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Okada, Ryuichi, Toshinori Watanabe, Seiji Uzawa, Takehiro Himeno, and Tsutomu Oishi. "Influence of Microjet Condition on Characteristics of Supersonic Jet Noise and Flow Field." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-68821.

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Jet noise reduction is essential for environmentally-friendly civil transport. Since jet noise becomes very intense in the case of supersonic aircraft, noise reduction is crucial topic for the realization of next-generation supersonic transport. In the present study, experimental investigations were performed to clarify the effect of microjet injection on supersonic jet noise and flow field. The experiments were focused on supersonic jet with Mach number up to 1.47, which was generated from a rectangular nozzle with high aspect ratio. Far-field acoustic measurements were conducted for widely r
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Kempf, Severin G., Stephen Guillot, Wing Fai Ng, Steven R. Wellborn, and Randall M. Chriss. "Numerical Study of Embedded Supersonic Compressor Stages." In ASME Turbo Expo 2005: Power for Land, Sea, and Air. ASMEDC, 2005. http://dx.doi.org/10.1115/gt2005-68611.

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A numerical case study of a multistage, highly-loaded, relative supersonic compressor is presented. The purpose of the investigation was to highlight the changing shock structure while throttling the compressor and to give insight into possible compressor instabilities. The computational fluid dynamic (CFD) study was conducted with the NASA code ADPAC, utilizing the mixing-plane assumption for the boundary condition between adjacent, relatively-rotating blade rows. A steady, five-blade-row, numerical simulation using the Baldwin-Lomax turbulence model was performed, creating several constant s
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Lou, Fangyuan, Herbert M. Harrison, William J. Brown, and Nicole L. Key. "Investigation of Surge in a Transonic Centrifugal Compressor With Vaned Diffuser: Part 2 – Correlation With Subcomponent Characteristics." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-82686.

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Abstract In the first part of the paper, surge signatures and the underlying mechanisms thereof for a high-speed centrifugal compressor were investigated using signals from fast-response transducers installed along the flow path. The compressor surge signature is observed to vary as the impeller inlet tip flow transitions from subsonic to supersonic conditions. Spike-type deep surge is observed at subsonic and supersonic impeller inlet tip conditions while modal-type mild surge occurs at 90% speed with transonic inlet tip conditions. In Part 2 of the paper, a detailed analysis of the static pr
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Degroote, Joris, Ine Hertens, Akil Osman, and Jan Vierendeels. "Simulation of the Interaction Between a Slender Flexible Cylinder and an Axial High-Speed Air Flow." In ASME 2017 Pressure Vessels and Piping Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/pvp2017-65967.

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This research analyzes the interaction between fibers and the air jets that are used to accelerate them in fiber processing industries. Typically, supersonic flow is used to achieve sufficiently high thread speeds. However, this flow contains shocks and expansions, resulting in large longitudinal variations in force on the thin and flexible thread. Consequently, a complex fluid-structure interaction (FSI) occurs between the supersonic air flow and the thread. In this research, the fluid-structure interaction between a supersonic air flow and a thread is studied numerically using three-dimensio
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Theofanous, T. G., G. J. Li, and T. N. Dinh. "Aerobreakup in Rarefied Supersonic Gas Flows (Keynote)." In ASME/JSME 2003 4th Joint Fluids Summer Engineering Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/fedsm2003-45549.

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We present new experimental results on the interfacial instabilities and breakup of Newtonian liquid drops suddenly exposed to rarefied, high-speed (Mach 3) air flows. The experimental approach allows for the first time detailed observation of interfacial phenomena and mixing throughout the breakup cycle over a wide range of Weber numbers. Key findings are that Rayleigh-Taylor instability alone is the active mechanism for free stream Weber numbers as low as 28 for low viscosity liquids and that stripping rather than piercing is the asymptotic regime as We→∞. This and other detailed visual evid
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Karp, I., and A. Rudoy. "Spraying Coatings by Supersonic Metallization." In ITSC 2000, edited by Christopher C. Berndt. ASM International, 2000. http://dx.doi.org/10.31399/asm.cp.itsc2000p0643.

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Abstract A technology and a specialized equipment complex based on supersonic arc spraying gun, where a supersonic stream of combustion products of hydrocarbon-gas (HC-gas) with air is used as an atomizing gas, have been developed. Durable and safe work of coated parts functioning under conditions of intensive loading is determined (except general requirement to coatings: wear resistance, hardness) to a large extent by the fatigue strength, porosity and stability of the properties of coatings. New possibilities for satisfying all the requirement to coatings on parts type are opened up by a hig
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Greska, Brenton J., and Anjaneyulu Krothapalli. "High Temperature Supersonic Jet Facility for Aeroacoustic Studies." In ASME 2001 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2001. http://dx.doi.org/10.1115/imece2001/nca-23503.

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Abstract This paper describes a newly built experimental facility at the Florida State University to develop innovative technologies for the noise suppression and mixing control of high-speed jets. This facility is capable of generating jet flows up to a maximum jet exit Mach number of about 2.5 at stagnation temperatures reaching up to 1500K. The facility can accommodate nozzles having an exit diameter of about 80 mm. At the maximum operating conditions, the jet can be run continuously for about 15 minutes. The jet exhausts into an anechoic room that measures 5.2 m (width) × 5.8 m (length) ×
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