Relevant bibliographies by topics / Free-piston driven shock tunnel

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Academic literature on the topic 'Free-piston driven shock tunnel'

Author: Grafiati
Published: 6 September 2023
Last updated: 31 July 2025

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Journal articles on the topic "Free-piston driven shock tunnel"

1

Macrossan, M. N. "Hypervelocity flow of dissociating nitrogen downstream of a blunt nose." Journal of Fluid Mechanics 217 (August 1990): 167–202. http://dx.doi.org/10.1017/s0022112090000672.

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The nature of the non-equilibrium flow of strongly dissociating nitrogen has been investigated by a series of simulation calculations using non-equilibrium (finite rate) chemical reactions. These were made with the equilibrium flux method (EFM), and the results have been found to compare favourably with experimental results obtained with a free-piston driven shock-tube wind tunnel which was used to obtain interferograms of the flow of pure nitrogen over a blunt-nosed body, 65 mm long at three angles of incidence. No simple relation between the flow with non-equilibrium chemistry and those for
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Chang, Eric Won Keun, Wilson Y. K. Chan, Keill J. Hopkins, Timothy J. McIntyre, and Ananthanarayanan Veeraragavan. "Electrically-heated flat plate testing in a free-piston driven shock tunnel." Aerospace Science and Technology 103 (August 2020): 105856. http://dx.doi.org/10.1016/j.ast.2020.105856.

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Stalker, R. J. "Modern developments in hypersonic wind tunnels." Aeronautical Journal 110, no. 1103 (2006): 21–39. http://dx.doi.org/10.1017/s0001924000004346.

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AbstractThe development of new methods of producing hypersonic wind-tunnel flows at increasing velocities during the last few decades is reviewed with attention to airbreathing propulsion, hypervelocity aerodynamics and superorbital aerodynamics. The role of chemical reactions in these flows leads to use of a binary scaling simulation parameter, which can be related to the Reynolds number, and which demands that smaller wind tunnels require higher reservoir pressure levels for simulation of flight phenomena. The use of combustion heated vitiated wind tunnels for propulsive research is discusse
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ITOH, Katsuhiro, Tomoyuki KOMURO, Kazuo SATO, Shuichi UEDA, Hideyuki TANNO, and Masahiro TAKAHASHI. "Characteristics of Free-Piston Shock Tunnel HIEST. 1st Report. Tuned Operation of Free-Piston Driver." Transactions of the Japan Society of Mechanical Engineers Series B 68, no. 675 (2002): 2968–75. http://dx.doi.org/10.1299/kikaib.68.2968.

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Itoh, K., S. Ueda, T. Komuro, et al. "Improvement of a free piston driver for a high-enthalpy shock tunnel." Shock Waves 8, no. 4 (1998): 215–33. http://dx.doi.org/10.1007/s001930050115.

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Boyce, R. R., M. Takahashi, and R. J. Stalker. "Mass spectrometric measurements of driver gas arrival in the T4 free-piston shock-tunnel." Shock Waves 14, no. 5-6 (2005): 371–78. http://dx.doi.org/10.1007/s00193-005-0276-3.

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Jacobs, P. A., and R. J. Stalker. "Mach 4 and Mach 8 axisymmetric nozzles for a high-enthalpy shock tunnel." Aeronautical Journal 95, no. 949 (1991): 324–34. http://dx.doi.org/10.1017/s0001924000024209.

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AbstractThis study examines the performance of two axisymmetric nozzles which were designed to produce uniform, parallel flow with nominal Mach numbers of 4 and 8. A free-piston-driven shock tube was used to supply the nozzle with high-temperature, high-pressure test gas. The inviscid design procedure treated the nozzle expansion in two stages. Close to the nozzle throat, the nozzle wall was specified as conical and the gas flow was treated as a quasi-one-dimensional chemically-reacting flow. At the end of the conical expansion, the gas was assumed to be calorically perfect and a contoured wal
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Sandham, N. D., E. Schülein, A. Wagner, S. Willems, and J. Steelant. "Transitional shock-wave/boundary-layer interactions in hypersonic flow." Journal of Fluid Mechanics 752 (July 4, 2014): 349–82. http://dx.doi.org/10.1017/jfm.2014.333.

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AbstractStrong interactions of shock waves with boundary layers lead to flow separations and enhanced heat transfer rates. When the approaching boundary layer is hypersonic and transitional the problem is particularly challenging and more reliable data is required in order to assess changes in the flow and the surface heat transfer, and to develop simplified models. The present contribution compares results for transitional interactions on a flat plate at Mach 6 from three different experimental facilities using the same instrumented plate insert. The facilities consist of a Ludwieg tube (RWG)
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Tani, K., K. Itoh, M. Takahashi, H. Tanno, T. Komuro, and H. Miyajima. "Numerical study of free-piston shock tunnel performance." Shock Waves 3, no. 4 (1994): 313–19. http://dx.doi.org/10.1007/bf01415829.

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Jacobs, P. A. "Quasi-one-dimensional modeling of a free-piston shock tunnel." AIAA Journal 32, no. 1 (1994): 137–45. http://dx.doi.org/10.2514/3.11961.

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Dissertations / Theses on the topic "Free-piston driven shock tunnel"

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Rousset, Bernard Hornung H. G. Hornung H. G. "Calibration and study of the contoured nozzle of the T5 free-piston hypervelocity shock tunnel /." Diss., Pasadena, Calif. : California Institute of Technology, 1995. http://resolver.caltech.edu/CaltechETD:etd-10192007-094437.

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Deep, Sneh. "Characterization of high enthalpy flows in the IISc free-piston driven shock tunnel using Two-Colour Ratio Pyrometry." Thesis, 2019. https://etd.iisc.ac.in/handle/2005/4601.

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High temperature and its associated effects set the hypersonic flow regime apart from other class of flows. Viscous dissipation raises the internal energy of the high-kinetic-energy gas as it slows down in the boundary layer. For slow heat conduction into the vehicle surface, the gas temperature increases drastically, leading to real gas effects, dissociation and ionization of molecules. Due to the thickened boundary layer, strong ‘viscous interaction’ exists between the outer inviscid shock layer and the boundary layer, leading to a pressure rise compared to an inviscid case. This pressure in
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Jayaram, V. "Experimental Investigations Of Surface Interactions Of Shock Heated Gases On High Temperature Materials Using High Enthalpy Shock Tubes." Thesis, 2007. https://etd.iisc.ac.in/handle/2005/495.

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The re-entry space vehicles encounter high temperatures when they enter the earth atmosphere and the high temperature air in the shock layer around the body undergoes partial dissociation. Also, the gas molecules injected into the shock layer from the ablative thermal protection system (TPS) undergo pyrolysis which helps in reducing the net heat flux to the vehicle surface. The chemical species due to the pyrolysis add complexity to the stagnation flow chemistry (52 chemical reactions) models which include species like NOx, CO and hydrocarbons (HCs). Although the ablative TPS is responsible fo
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Jayaram, V. "Experimental Investigations Of Surface Interactions Of Shock Heated Gases On High Temperature Materials Using High Enthalpy Shock Tubes." Thesis, 2007. http://hdl.handle.net/2005/495.

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The re-entry space vehicles encounter high temperatures when they enter the earth atmosphere and the high temperature air in the shock layer around the body undergoes partial dissociation. Also, the gas molecules injected into the shock layer from the ablative thermal protection system (TPS) undergo pyrolysis which helps in reducing the net heat flux to the vehicle surface. The chemical species due to the pyrolysis add complexity to the stagnation flow chemistry (52 chemical reactions) models which include species like NOx, CO and hydrocarbons (HCs). Although the ablative TPS is responsible fo
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Thakur, Ruchi. "Experimental Analysis of Shock Stand off Distance over Spherical Bodies in Hypersonic Flows." Thesis, 2015. http://etd.iisc.ac.in/handle/2005/3848.

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One of the characteristics of the high speed ows over blunt bodies is the detached shock formed in front of the body. The distance of the shock from the stagnation point measured along the stagnation streamline is termed as the shock stand o distance or the shock detachment distance. It is one of the most basic parameters in such ows. The need to know the shock stand o distance arises due to the high temperatures faced in these cases. The biggest challenge faced in high enthalpy ows is the high amounts of heat transfer to the body. The position of the shock is relevant in knowing the temperatu
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Thakur, Ruchi. "Experimental Analysis of Shock Stand off Distance over Spherical Bodies in Hypersonic Flows." Thesis, 2015. http://etd.iisc.ernet.in/2005/3848.

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One of the characteristics of the high speed ows over blunt bodies is the detached shock formed in front of the body. The distance of the shock from the stagnation point measured along the stagnation streamline is termed as the shock stand o distance or the shock detachment distance. It is one of the most basic parameters in such ows. The need to know the shock stand o distance arises due to the high temperatures faced in these cases. The biggest challenge faced in high enthalpy ows is the high amounts of heat transfer to the body. The position of the shock is relevant in knowing the temperatu
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Srinath, S. "Development of Novel Heat Transfer Gauges Based on Large Carbon Clusters to Measure Total as well as Radiative Heat Flux for Planetary Entry Configurations in Hypersonic Shock Tunnels." Thesis, 2017. http://etd.iisc.ac.in/handle/2005/4243.

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The quest of travelling beyond earth, preludes with ground based experimental studies, detailed analysis and accurate calculations in the aspects of having a safer design of flying vehicles. As the vehicles plunge into the dense atmosphere with greater velocities to hypersonic Mach numbers, the shockwave produced ahead of the aerodynamic body becomes highly intense producing volatile conditions at a temperature of several thousands of Kelvins. Predominantly the unsteady effects are dominated by radiations in the velocities which are greater than 6km/s. During such high enthalpy flows, the atmo
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Pulford, David Robert Newman. "Coherent anti-Stokes Raman scattering in a free piston shock tunnel." Phd thesis, 1994. http://hdl.handle.net/1885/138398.

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Boyce, Russell Robert. "Computational fluid dynamics code validation using a free piston shock tunnel." Phd thesis, 1995. http://hdl.handle.net/1885/145378.

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Rousset, Bernard. "Calibration and study of the contoured nozzle of the T5 free-piston hypervelocity shock tunnel." Thesis, 1995. https://thesis.library.caltech.edu/4181/1/Rousset_b_1995.pdf.

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A pitot pressure survey of the contoured nozzle of the T5 shock tunnel was performed over a wide range of reservoir conditions and in the region of the exit plane of the nozzle. A rake of thirteen pitot probes was used for this purpose. The survey includes an investigation of the repeatability of the facility and an analysis of the accuracy of the measurements. The features of the pitot pressure distribution across the exit plane are a pronounced minimum near but not exactly on the centerline, and a pronounced drop near the nozzle wall. The concave profile may be quantified in terms of the cur
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Books on the topic "Free-piston driven shock tunnel"

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Hornung, H. G. Performance data of the new free-piston shock tunnel at GALCIT. AIAA, 1992.

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2

Maus, J. R. The G-Range Impulse Facility, a high-performance free-piston shock tunnel. AIAA, 1992.

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Book chapters on the topic "Free-piston driven shock tunnel"

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Mundt, Christian. "Development of the New Piston-Driven Shock-Tunnel HELM." In Experimental Methods of Shock Wave Research. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-23745-9_8.

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Stennett, S., D. E. Gildfind, and P. A. Jacobs. "Optimising the X3R Reflected Shock Tunnel Free-Piston Driver for Long Duration Test Times." In 31st International Symposium on Shock Waves 2. Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-319-91017-8_23.

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Schemperg, K., and C. Mundt. "On the free-piston shock tunnel at UniBwM (HELM)." In Shock Waves. Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-85168-4_76.

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Mitsuda, M., T. Oda, T. Kurosaka, S. Wakuri, and T. Arai. "One-Dimensional Simulation of Free-Piston Shock Tunnel/Expansion Tubes." In Shock Waves @ Marseille I. Springer Berlin Heidelberg, 1995. http://dx.doi.org/10.1007/978-3-642-78829-1_74.

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Hornung, H., B. Sturtevant, J. Bélanger, S. Sanderson, M. Brouillette, and M. Jenkins. "Performance data of the new free-piston shock tunnel T5 at GALCIT." In Shock Waves. Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-77648-9_95.

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Reddy, K. P. J., M. S. Hegde, and V. Jayaram. "Material processing and surface reaction studies in free piston driven shock tube." In Shock Waves. Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-85168-4_5.

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Jenkins, D. M., R. J. Stalker, and W. R. B. Morrison. "Performance considerations in the operation of free-piston driven hypersonic test facilities." In Shock Waves. Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-77648-9_94.

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Burtschell, Y., R. Brun, and D. Zeitoun. "Two dimensional numerical simulation of the Marseille university free piston shock tunnel-TCM2." In Shock Waves. Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-77648-9_92.

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Itoh, Katsuhiro, Kouichiro Tani, Hideyuki Tanno, et al. "A Numerical and Experimental Study of the Free Piston Shock Tunnel." In Shock Waves @ Marseille I. Springer Berlin Heidelberg, 1995. http://dx.doi.org/10.1007/978-3-642-78829-1_41.

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Shen, Junmou, Handong Ma, Chen Li, Xing Chen, and Bi Zhixian. "Initial Testing of a 2 m Mach-10 Free-Piston Shock Tunnel." In 31st International Symposium on Shock Waves 2. Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-319-91017-8_26.

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Conference papers on the topic "Free-piston driven shock tunnel"

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Cain, T. M., and R. J. Stalker. "A compression ignition driver for a free piston shock tunnel." In Current topics in shock waves 17th international symposium on shock waves and shock tubes Bethlehem, Pennsylvania (USA). AIP, 1990. http://dx.doi.org/10.1063/1.39485.

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Chang, E. W. K., W. Y. K. Chan, T. J. McIntyre, and A. Veeraragavan. "Hypersonic Shock Impingement on a Heated Surface in the T4 Free-Piston Driven Shock Tunnel." In Proceedings of the 32nd International Symposium on Shock Waves (ISSW32 2019). Research Publishing Services, 2019. http://dx.doi.org/10.3850/978-981-11-2730-4_0164-cd.

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Mundt, Ch, C. Selcan, and T. Sander. "Investigations in the piston Driven Shock-Tunnel HELM." In Proceedings of the 32nd International Symposium on Shock Waves (ISSW32 2019). Research Publishing Services, 2019. http://dx.doi.org/10.3850/978-981-11-2730-4_502-cd.

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Whitside, R. W., W. Y. K. Chan, D. E. Gildfind, M. K. Smart, and P. A. Jacobs. "Nitrogen Driver for Low-Enthalpy Testing in Free-Piston Driven Shock Tunnels." In Proceedings of the 32nd International Symposium on Shock Waves (ISSW32 2019). Research Publishing Services, 2019. http://dx.doi.org/10.3850/978-981-11-2730-4_0305-cd.

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Hongbo, Lu, Chen Xing, Li Chen, et al. "Preliminary commissioning of hydrogen supersonic combustion in FD-21 free piston driven shock tunnel." In Proceedings of the 32nd International Symposium on Shock Waves (ISSW32 2019). Research Publishing Services, 2019. http://dx.doi.org/10.3850/978-981-11-2730-4_0248-cd.

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BELANGER, JACQUES, and HANS HORNUNG. "A combustion driven shock tunnel to complement the free piston shocktunnel T5 at GALCIT." In 28th Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-3968.

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Steer, Joseph, Peter L. Collen, Alex B. Glenn, et al. "Shock Radiation Tests for Ice Giant Entry Probes Including CH4 in the T6 Free-Piston Driven Wind Tunnel." In AIAA SCITECH 2023 Forum. American Institute of Aeronautics and Astronautics, 2023. http://dx.doi.org/10.2514/6.2023-1729.

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Burtschell, Y., P. Colas, P. Gubernatis, et al. "Numerical simulation of a free piston shock tunnel." In Current topics in shock waves 17th international symposium on shock waves and shock tubes Bethlehem, Pennsylvania (USA). AIP, 1990. http://dx.doi.org/10.1063/1.39486.

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Blanks, J., and J. DeWitt. "Calibration tests of AEDC free-piston shock tunnel." In 25th Plasmadynamics and Lasers Conference. American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-2526.

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Maus, J., J. Blanks, and J. Dewitt. "Calibration tests of a new free-piston shock tunnel." In 5th International Aerospace Planes and Hypersonics Technologies Conference. American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-5003.

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Reports on the topic "Free-piston driven shock tunnel"

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Stallings, D. W., W. D. Williams, and E. J. Felderman. Free-Piston Shock Tunnel Test Technique Development: An AEDC/DLR Cooperative Program. Defense Technical Information Center, 2003. http://dx.doi.org/10.21236/ada412642.

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