Relevant bibliographies by topics / High Enthalpy

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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 'High Enthalpy'

Author: Grafiati
Published: 4 June 2021
Last updated: 11 February 2022

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Journal articles on the topic "High Enthalpy"

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Pinto, Isabel, Helena Cardoso, Cecélia Leão, and N. van Uden. "High enthalpy and low enthalpy death inSaccharomyces cerevisiaeinduced by acetic acid." Biotechnology and Bioengineering 33, no. 10 (1989): 1350–52. http://dx.doi.org/10.1002/bit.260331019.

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Degrez, G., A. Lani, M. Panesi, O. Chazot, and H. Deconinck. "Modelling of high-enthalpy, high-Mach number flows." Journal of Physics D: Applied Physics 42, no. 19 (2009): 194004. http://dx.doi.org/10.1088/0022-3727/42/19/194004.

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Chanetz, Bruno, Thierry Pot, Reynald Bur, et al. "High-enthalpy hypersonic project at ONERA." Aerospace Science and Technology 4, no. 5 (2000): 347–61. http://dx.doi.org/10.1016/s1270-9638(00)00145-0.

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Ershov, A. P., A. O. Kashkarov, and E. R. Pruuel. "Physical mechanisms of high-enthalpy initiation." Combustion, Explosion, and Shock Waves 51, no. 6 (2015): 700–709. http://dx.doi.org/10.1134/s0010508215060118.

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Mallinson, S. G., S. L. Gai, and N. R. Mudford. "High-enthalpy, hypersonic compression corner flow." AIAA Journal 34, no. 6 (1996): 1130–37. http://dx.doi.org/10.2514/3.13203.

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BELEVTSEV, ANDREI A., RUBEN R. GRIGOR'YANTS, EMIN KH ISAKAEV, PETER P. IVANOV, ALEXANDER V. MARKIN, and VALERY F. CHINNOV. "Study of High Enthalpy Plasma Flows." Annals of the New York Academy of Sciences 891, no. 1 HEAT AND MASS (1999): 360–67. http://dx.doi.org/10.1111/j.1749-6632.1999.tb08784.x.

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Bonelli, Francesco, Michele Tuttafesta, Gianpiero Colonna, Luigi Cutrone, and Giuseppe Pascazio. "Numerical Investigation of High Enthalpy Flows." Energy Procedia 126 (September 2017): 99–106. http://dx.doi.org/10.1016/j.egypro.2017.08.128.

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Duan, L., and M. P. Martín. "Direct numerical simulation of hypersonic turbulent boundary layers. Part 4. Effect of high enthalpy." Journal of Fluid Mechanics 684 (September 6, 2011): 25–59. http://dx.doi.org/10.1017/jfm.2011.252.

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AbstractIn this paper we present direct numerical simulations (DNS) of hypersonic turbulent boundary layers to study high-enthalpy effects. We study high- and low-enthalpy conditions, which are representative of those in hypersonic flight and ground-based facilities, respectively. We find that high-enthalpy boundary layers closely resemble those at low enthalpy. Many of the scaling relations for low-enthalpy flows, such as van-Driest transformation for the mean velocity, Morkovin’s scaling and the modified strong Reynolds analogy hold or can be generalized for high-enthalpy flows by removing the calorically perfect-gas assumption. We propose a generalized form of the modified Crocco relation, which relates the mean temperature and mean velocity across a wide range of conditions, including non-adiabatic cold walls and real gas effects. The DNS data predict Reynolds analogy factors in the range of those found in experimental data at low-enthalpy conditions. The gradient transport model approximately holds with turbulent Prandtl number and turbulent Schmidt number of order unity. Direct compressibility effects remain small and insignificant for all enthalpy cases. High-enthalpy effects have no sizable influence on turbulent kinetic energy (TKE) budgets or on the turbulence structure.
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Chirkova, V. Yu, Ye A. Sharlayeva, and I. Ye Stas. "Boiling temperature and the enthalpy of water vaporization exposed to high frequency electromagnetic field." Bulletin of the Karaganda University. "Chemistry" series 94, no. 2 (2019): 51–55. http://dx.doi.org/10.31489/2019ch2/51-55.

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Jeong, Dahai, Brian K. Haus, and Mark A. Donelan. "Enthalpy Transfer across the Air–Water Interface in High Winds Including Spray." Journal of the Atmospheric Sciences 69, no. 9 (2012): 2733–48. http://dx.doi.org/10.1175/jas-d-11-0260.1.

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Abstract Controlled experiments were conducted in the Air–Sea Interaction Saltwater Tank (ASIST) at the University of Miami to investigate air–sea moist enthalpy transfer rates under various wind speeds (range of 0.6–39 m s−1 scaled to equivalent 10-m neutral winds) and water–air temperature differences (range of 1.3°–9.2°C). An indirect calorimetric (heat content budget) measurement technique yielded accurate determinations of moist enthalpy flux over the full range of wind speeds. These winds included conditions with significant spray generation, the concentrations of which were of the same order as field observations. The moist enthalpy exchange coefficient so measured included a contribution from cooled reentrant spray and therefore serves as an upper limit for the interfacial transfer of enthalpy. An unknown quantity of spray was also observed to exit the tank without evaporating. By invoking an air volume enthalpy budget it was determined that the potential contribution of this exiting spray over an unbounded water volume was up to 28%. These two limits bound the total enthalpy transfer coefficient including spray-mediated transfers.
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Dissertations / Theses on the topic "High Enthalpy"

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Armani, Silvia. "High-enthalpy geothermal reservoir model calibration using PEST." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2017. http://amslaurea.unibo.it/13293/.

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The main purpose of this thesis work is focused on the use of PEST (Parameter Estimation) to calibrate numerical models of High Enthalpy Geothermal Reservoirs (HEGR). PEST is a parameter estimation and analysis of the uncertainties of complex numerical models tool, that can be instructed to work with a standalone simulator. So, the T2Well-EWASG was used as coupled wellbore-reservoir simulator for multiphase-multicomponent HEGR. The idea of this thesis work is that the possibility to implement some automation degrees in the wellbore-reservoir model calibration task would improve substantially the Reservoir Engineers work. To become familiar with PEST, it has been necessary a preliminary training to learn how to manage its input files, its keywords, and the utility programs having the function of verifying the correctness and consistency of the created files. Then, one of the examples of PEST manual (which Fortran source code is supplied) was reproduced and analyzed, and subsequently modified. In particular, starting from this example, a simple linear model with two free parameters, some changes have been performed: "fixing" a parameter to inhibit its change during the calibration; reading a more complex model output file respect to the original example; inserting dummy data that should not be processed and instructing PEST to consider only the data of interest; changing the model adding parameters to be calibrated, and including them in the analysis changing the PEST inputs files. Finally, these skills were applied to use PEST with T2Well-EWASG to calibrate a numerical model, relative to a real HEGR, previously calibrated via a trial and error approach in a PhD thesis work. Among the real data used there were also short production-tests done in a geothermal field located in the Dominica Commonwealth. The preliminary results show that the PEST-T2Well-EWASG calibration system works fine, and that it is a useful tool that can improve the work of reservoir engineering.
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Hamilton, Christianne Rhea. "Design of Test Sections for a High Enthalpy Wind Tunnel." MSSTATE, 2003. http://sun.library.msstate.edu/ETD-db/theses/available/etd-04082003-114126/.

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This document describes the design of a supersonic and a subsonic test section for a high enthalpy wind tunnel. A streamline is tracked through a supersonic test section using the method of characteristics. The specifics of the design program and the design techniques are illustrated for the supersonic section. The section of the paper dealing with the subsonic nozzle has a greatly diverse nature. This section details the inlet and exhaust restrictions and construction elements for the entire low speed system. The system is currently being set up for testing with the subsonic section, and the supersonic will eventually follow.
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Meritt, Ryan James. "Skin Friction Sensor Design Methodology and Validation for High-Speed, High-Enthalpy Flow Applications." Diss., Virginia Tech, 2014. http://hdl.handle.net/10919/54569.

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This investigation concerns the design, build, and testing of a new class of skin friction sensor capable of performing favorably in high-speed, high-enthalpy flow conditions, such as that found in atmospheric re-entry vehicles, scramjets, jet engines, material testing, and industrial processes. Fully understanding and optimizing these complex flows requires an understanding of aerodynamic properties at high enthalpies, which, in turn, requires numerical and analytical modeling as well as reliable diagnostic instrumentation. Skin friction is a key quantity in assessing the overall flight and engine performance, and also plays an important role in identifying and correcting problem areas. The sensor design is founded on a direct-measuring, cantilever arrangement. The design incorporates two fundamental types of materials in regards to thermal conductivity and voltage resistivity properties. The non-conducting material distinction greatly deters the effect of heat soak and prevents EMI transmission throughout the sensor. Four custom fabricated metal-foil strain gauges are arranged in a Wheatstone bridge configuration to increase sensitivity and to provide further compensation for sensitivity effects. The sensor is actively cooled via a copper water channel to minimize the temperature gradient across the electronic systems. The design offers a unique immunity to many of the interfering influences found in complex, high-speed, high-enthalpy flows that would otherwise overshadow the desired wall shear measurement. The need to develop an encompassing design methodology was recognized and became a principal focus of this research effort. The sensor design was developed through a refined, multi-disciplinary approach. Concepts were matured through an extensive and iterative program of evolving key performance parameters. Extensive use of finite element analysis (FEA) was critical to the design and analysis of the sensor. A software package was developed to utilize the powerful advantage of FEA methods and optimization techniques over the traditional trial and error methods. Each sensor endured a thorough series of calibrations designed to systematically evaluate individual aspects of its functionality in static, dynamic, pressure, and thermal responses. Bench-test facilities at Virginia Tech (VT) and Air Force Research Laboratory (AFRL) further characterized the design vibrational effects and electromagnetic interference countermeasure effectiveness. Through iterations of past designs, sources of error have been identified, controlled, and minimized. The total uncertainty of the skin friction sensor measurement capability was determined to be ±8.7% at 95% confidence and remained fairly independent of each test facility. A rigorous, multi-step approach was developed to systematically test the skin friction sensor in various facilities, where flow enthalpy and run duration were progressively increased. Initial validation testing was conducted at the VT Hypersonic Tunnel. Testing at AFRL was first performed in the RC-19 facility under high-temperature, mixing flow conditions. Final testing was conducted under simulated scramjet flight conditions in the AFRL RC-18 facility. Performance of the skin friction sensors was thoroughly analyzed across all three facilities. The flow stagnation enthalpies upward of 1053 kJ/kg (453 Btu/lbm) were tested. A nominal Mach 2.0 to 3.0 flow speed range was studied and stagnation pressure ranged from 172 to 995 kPa (25 to 144 psia). Wall shear was measured between 94 and 750 Pa (1.96 and 15.7 psf). Multiple entries were conducted at each condition with good repeatability at ±5% variation. The sensor was also able to clearly indicate the transient flow conditions of a full scramjet combustion operability cycle to include shock train movement and backflow along the isolator wall. The measured experimental wall shear data demonstrated good agreement with simple, flat-plate analytical estimations and historic data (where available). Numerical CFD predictions of the scramjet flow path gave favorable results for steady cold and hot flow conditions, but had to be refined to handle the various fueling injection schemes with burning in the downstream combustor and surface roughness models. In comparing CFD wall shear predictions to the experimental measurements, in a few cases, the sensor measurement was adversely affected by shock and complex flow interaction. This made comparisons difficult for these cases. The sensor maintained full functionality under sustained high-enthalpy conditions. No degradation in performance was noted over the course of the tests. This dissertation research and development program has proven successful in advancing the development of a skin friction sensor for applications in high-speed, high-enthalpy flows. The sensor was systematically tested in relevant, high-fidelity laboratory environments to demonstrate its technology readiness and to successfully achieve a technology readiness level (TRL) 6 milestone. The instrumentation technology is currently being transitioned from laboratory development to the end users in the hypersonic test community.<br>Ph. D.
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Lutz, Andrew. "Experimental Investigation And Analysis Of High-Enthalpy Nitrogen Flow Over Graphite." ScholarWorks @ UVM, 2015. http://scholarworks.uvm.edu/graddis/361.

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The high-enthalpy flow generated by hypersonic vehicles traveling within the Earth's atmosphere inherently delivers an elevated heat flux to the vehicle surface. In addition to conductive heating, the liberated energy generated by various exothermic chemical reactions occurring at the vehicle surface further augment the total heat load. Quantifying the rates at which these reactions take place is imperative and remains a significant challenge as developers attempt to design the next generation of thermal protection systems. This study focused on nitrogen recombination and carbon nitridation, as these reactions are ubiquitous to the most aggressive atmospheric re-entry trajectories in which carbon-based ablative heat shields are conventionally employed. The 30-kW inductively coupled plasma torch located within the Plasma Diagnostics and Test Laboratory at the University of Vermont was used to produce high-enthalpy nitrogen plasma flow, which sufficiently simulated the various in-flight heat flux processes. A combination of optical-based techniques, including spontaneous emission spectroscopy and laser induced fluorescence were utilized to study the free jet and the interaction of the flow with samples constructed from POCO graphite. Emission measurements within the free stream indicated that the nitrogen flow was in non-equilibrium due to the inverse predissociation of ground state nitrogen atoms into the v = 13 vibrational level of the molecular nitrogen electronic B-state. The degree of non-equilibrium was quantified by determining the overpopulation of ground state nitrogen with respect to equilibrium and its effects were considered throughout the analysis. Results obtained through emission spectroscopy and laser induced fluorescence confirmed that the graphite material behaved as a catalytic surface that actively promoted nitrogen recombination. Additionally, the calculated carbon nitridation rate was several orders less efficient, although its effect on the sample surface erosion was evident in the sample mass loss measurements. Subsequently, an independent set of heat flux measurements performed over materials of varying catalycities further supported the data obtained with optical diagnostics. Furthermore, the heat flux results yielded the surface accommodation factor of graphite for the nitrogen recombination rate and indicated that the surface was slightly less than fully-accommodating.
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Meritt, Ryan James. "A Study of Direct Measuring Skin Friction Gages for High Enthalpy Flow Applications." Thesis, Virginia Tech, 2010. http://hdl.handle.net/10919/76783.

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This study concerns the design, analysis, and initial testing of a novel skin friction gage for applications in three-dimensional, high-speed, high-enthalpy flows. Design conditions required favorable gage performance in the Arc-Heated Facilities at Arnold Engineering Development Center. Flow conditions are expected to be at Mach 3.4, with convective heat properties of h= 1,500 W/(m°·K) (264 Btu/(hr·ft°·°R)) and T_aw= 3,900 K (7,000 °R). The wall shear stress is expected to be as high as τ_w= 2,750 Pa (0.40 psi) with a correlating coefficient of skin friction value around C_f= 0.0035. Through finite element model and analytical analyses, a generic gage design is predicted to remain fully functional and within reasonable factors of safety for short duration tests. The deflection of the sensing head does not exceed 0.025 mm (0.0001 in). Surfaces exposed to the flow reach a maximum temperatures of 960 K (1,720 °R) and the region near the sensitive electronic components experience a negligible rise in temperature after a one second test run. The gage is a direct-measuring, non-nulling design in a cantilever beam arrangement. The sensing head is flush with the surrounding surface of the wall and is separated by a small gap, approximately 0.127 mm (0.005 in). A dual-axis, semi-conductor strain gage unit measures the strain in the beam resulting from the shear stress experienced by the head due to the flow. The gage design incorporates a unique bellows system as a shroud to contain the oil filling and protect the strain gages. Oil filling provides dynamic and thermal damping while eliminating uniform pressure loading. An active water-cooling system is routed externally around the housing in order to control the temperature of the gage system and electronic components. Each gage is wired in a full-bridge Wheatstone configuration and is calibrated for temperature compensation to minimize temperature effects. Design verification was conducted in the Virginia Tech Hypersonic Tunnel. The gage was tested in well-documented Mach 3.0, cold and hot flow environments. The tunnel provided stagnation temperatures and pressures of up to T₀= 655 K (1,180 °R) and P₀= 1,020 kPa (148 psi) respectively. The local wall temperatures ranged from T_w= 292 to 320 K (525 to 576 °R). The skin friction coefficient measurements were between 0.00118 and 0.00134 with an uncertainty of less than 5%. Results were shown to be repeatable and in good concurrence with analytical predictions. The design concept of the gage proved to be very sound in heated, supersonic flow. When it worked, it did so very effectively. Unfortunately, the implementation of the concept is still not robust enough for routine use. The strain gage units in general were often unstable and proved to be insufficiently reliable. The detailed gage design as built was subject to many potential sources of assembly misalignment and machining tolerances, and was susceptible to pre-loading. Further recommendations are provided for a better implementation of this design concept to make a fully functional gage test ready for Arnold Engineering Development Center.<br>Master of Science
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Simmons, Russell. "Direct Simulation Monte Carlo modelling of surface catalytic events in high enthalpy rarefied gas flows." Thesis, University of Oxford, 1996. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.318865.

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Salemi, Leonardo da Costa, and Leonardo da Costa Salemi. "Numerical Investigation of Hypersonic Conical Boundary-Layer Stability Including High-Enthalpy and Three-Dimensional Effects." Diss., The University of Arizona, 2016. http://hdl.handle.net/10150/621854.

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The spatial stability of hypersonic conical boundary layers is investigated utilizing different numerical techniques. First, the development and verification of a Linearized Compressible Navier-Stokes solver (LinCS) is presented, followed by an investigation of different effects that affect the stability of the flow in free-flight/ground tests, such as: high-enthalpy effects, wall-temperature ratio, and three-dimensionality (i.e. angle-of-attack). A temporally/spatially high-order of accuracy parallelized Linearized Compressible Navier-Stokes solver in disturbance formulation was developed, verified and employed in stability investigations. Herein, the solver was applied and verified against LST, PSE and DNS, for different hypersonic boundary-layer flows over several geometries (e.g. flat plate - M=5.35 & 10; straight cone - M=5.32, 6 & 7.95; flared cone - M=6; straight cone at AoA = 6 deg - M=6). The stability of a high-enthalpy flow was investigated utilizing LST, LinCS and DNS of the experiments performed for a 5 deg sharp cone in the T5 tunnel at Caltech. The results from axisymmetric and 3D wave-packet investigations in the linear, weakly, and strongly nonlinear regimes using DNS are presented. High-order spectral analysis was employed in order to elucidate the presence of nonlinear couplings, and the fundamental breakdown of second mode waves was investigated using parametric studies. The three-dimensionality of the flow over the Purdue 7 deg sharp cone at M=6 and AoA =6 deg was also investigated. The development of the crossflow instability was investigated utilizing suction/blowing at the wall in the LinCS/DNS framework. Results show good agreement with previous computational investigations, and that the proper basic flow computation/formation of the vortices is very sensitive to grid resolution.
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Chadwick, Kenneth Michael. "An actively cooled floating element skin friction balance for direct measurement in high enthalpy supersonic flows." Diss., This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-07282008-134703/.

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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.<br>Ph. D.
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Rini, Pietro. "Analysis of differential diffusion phenomena in high enthalpy flows, with application to thermal protection material testing in ICP facilities." Doctoral thesis, Universite Libre de Bruxelles, 2006. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/210893.

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This thesis presents the derivation of the theory leading to the determination of the governing equations of chemically reacting flows under local thermodynamic equilibrium, which rigorously takes into account effects of elemental (de)mixing. As a result, new transport coefficients appear in the equations allowing a quantitative predictions and helping to gain deeper insight into the physics of chemically reacting flows at and near local equilibrium. These transport coefficients have been computed for both air and carbon dioxide mixtures allowing the application of this theory to both Earth and Mars entry problems in the framework of the methodology for the determination of the catalytic activity of Thermal Protections Systems (TPS) materials.<p>Firstly, we analyze the influence of elemental fraction variations on the computation of thermochemical equilibrium flows for both air and carbon dioxide mixtures. To this end, the equilibrium computations are compared with several chemical regimes to better analyze the influence of chemistry on wall heat flux and to observe the elemental fractions behavior along a stagnation line. The results of several computations are presented to highlight the effects of elemental demixing on the stagnation point heat flux and chemical equilibrium composition for air and carbon dioxide mixtures. Moreover, in the chemical nonequilibrium computations, the characteristic time of chemistry is artificially decreased and in the limit the chemical equilibrium regime, with variable elemental fractions, is achieved. Then, we apply the closed form of the equations governing the behavior of local thermodynamic equilibrium flows, accounting for the variation in local elemental concentrations in a rigorous manner, to simulate heat and mass transfer in CO2/N2 mixtures. This allows for the analysis of the boundary layer near the stagnation point of a hypersonic vehicle entering the true Martian atmosphere. The results obtained using this formulation are compared with those obtained using a previous form of the equations where the diffusive fluxes of elements are computed as a linear combination of the species diffusive fluxes. This not only validates the new formulation but also highlights its advantages with respect to the previous one :by using and analyzing the full set of equilibrium transport coefficients we arrive at a deep understanding of the mass and heat transfer for a CO2/N2 mixture.<p>Secondly, we present and analyze detailed numerical simulations of high-pressure inductively coupled air plasma flows both in the torch and in the test chamber using two different mathematical formulations: an extended chemical non-equilibrium formalism including finite rate chemistry and a form of the equations valid in the limit of local thermodynamic equilibrium and accounting for the demixing of chemical elements. Simulations at various operating pressures indicate that significant demixing of oxygen and nitrogen occurs, regardless of the degree of nonequilibrium in the plasma. As the operating pressure is increased, chemistry becomes increasingly fast and the nonequilibrium results correctly approach the results obtained assuming local thermodynamic equilibrium, supporting the validity of the proposed local equilibrium formulation. A similar analysis is conducted for CO2 plasma flows, showing the importance of elemental diffusion on the plasma behavior in the VKI plasmatron torch.<p>Thirdly, the extension of numerical tools developed at the von Karman Institute, required within the methodology for the determination of catalycity properties for thermal protection system materials, has been completed for CO2 flows. Non equilibrium stagnation line computations have been performed for several outer edge conditions in order to analyze the influence of the chemical models for bulk reactions. Moreover, wall surface reactions have been examined, and the importance of several recombination processes has been discussed. This analysis has revealed the limits of the model currently used, leading to the proposal of an alternative approach for the description of the flow-surface interaction. Finally the effects of outer edge elemental fractions on the heat flux map is analyzed, showing the need to add them to the list of parameters of the methodology currently used to determine catalycity properties of thermal protection materials.<br>Doctorat en sciences appliquées<br>info:eu-repo/semantics/nonPublished
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Books on the topic "High Enthalpy"

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Rathakrishnan, Ethirajan. High Enthalpy Gas Dynamics. John Wiley & Sons, Singapore Pte. Ltd, 2015. http://dx.doi.org/10.1002/9781119113126.

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Groenig, H. High enthalpy testing in hypersonic shock tunnels. Shock Wave Laboratory, Technical University Aachen, 1988.

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Ferrante, M. J. High-temperature relative enthalpies of V₂0₅. U.S. Dept. of the Interior, Bureau of Mines, 1986.

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Wilson, Gregory J. Time-dependent quasi-one-dimensional simulations of high enthalpy pulse facilities. American Institute of Aeronautics and Astronautics, 1992.

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Hannemann, Klaus. Design of an axisymmetric, contoured nozzle for the HEG. Deutsche Forschungsanstalt fur Luft- und Raumfahrt, 1990.

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Neumann, Richard D. Requirements in the 1990's for high enthalpy, ground test facilities for CFD validation. American Institute of Aeronautics and Astronautics, 1990.

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Lewis, Beverly W. Mass spectrometric gas composition measurements associated with jet interaction tests in a high-enthalpy wind tunnel. Langley Research Center, 1986.

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Kopp, Robert William. Determination of the velocity, density, mass flux and enthalpy profiles for very high temperature arc jet nozzle flow. Naval Postgraduate School, 1989.

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Rathakrishnan, Ethirajan. High Enthalpy Gas Dynamics. Wiley & Sons, Incorporated, John, 2014.

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Rathakrishnan, Ethirajan. High Enthalpy Gas Dynamics. Wiley & Sons, Incorporated, John, 2014.

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Book chapters on the topic "High Enthalpy"

1

Stober, Ingrid, and Kurt Bucher. "Geothermal Systems in High-Enthalpy Regions." In Geothermal Energy. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-71685-1_10.

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Djamali, Essmaiil, and Walter G. Chapman. "Chapter 20. Electrolyte Solutions: Standard State Partial Molar Enthalpies of Aqueous Solution up to High Temperatures." In Enthalpy and Internal Energy. Royal Society of Chemistry, 2017. http://dx.doi.org/10.1039/9781788010214-00521.

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Capitelli, Mario, Roberto Celiberto, Gianpiero Colonna, et al. "Non Equilibrium Plasma in High Enthalpy Flows." In Fundamental Aspects of Plasma Chemical Physics. Springer New York, 2016. http://dx.doi.org/10.1007/978-1-4419-8185-1_11.

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Esser, B., H. Grönig, and H. Olivier. "High-Enthalpy Testing in Hypersonic Shock Tunnels." In Advances in Hypersonics. Birkhäuser Boston, 1992. http://dx.doi.org/10.1007/978-1-4612-0379-7_5.

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Reimann, Bodo, Ian Johnston, and Volker Hannemann. "DLR τ-Code for High Enthalpy Flows." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer Berlin Heidelberg, 2004. http://dx.doi.org/10.1007/978-3-540-39604-8_13.

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Grönig, H. "Shock tube application: High enthalpy European wind tunnels." In Shock Waves. Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-77648-9_1.

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Beck, W. H., G. Eitelberg, T. J. McIntyre, J. P. Baird, J. Lacey, and H. Simon. "The high enthalpy shock tunnel in Göttingen (HEG)." In Shock Waves. Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-77648-9_106.

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Beck, W. H., G. Eitelberg, and T. J. McIntyre. "The High Enthalpy Shock Tunnel in Göttingen (HEG)." In Orbital Transport. Springer Berlin Heidelberg, 1993. http://dx.doi.org/10.1007/978-3-642-45720-3_19.

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Hornung, Hans. "Experimental Simulation of High-Enthalpy Real-Gas Effects." In Hypersonic Flows for Reentry Problems. Springer Berlin Heidelberg, 1991. http://dx.doi.org/10.1007/978-3-642-84580-2_12.

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Jiang, Z., H. R. Yu, and Z. B. Lin. "Research Progress on High-Enthalpy and Hypersonic Flows." In New Trends in Fluid Mechanics Research. Springer Berlin Heidelberg, 2007. http://dx.doi.org/10.1007/978-3-540-75995-9_7.

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Conference papers on the topic "High Enthalpy"

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Matsui, Makoto, Koji Shinmi, Kimiya Komurasaki, and Yoshihiro Arakawa. "Enthalpy Distributions of Laser Driven High Enthalpy Wind Tunnel." In 26th AIAA Aerodynamic Measurement Technology and Ground Testing Conference. American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-4133.

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Candler, Graham. "High enthalpy flow simulation challenges." In 29th AIAA, Plasmadynamics and Lasers Conference. American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-2749.

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Olejniczak, Joseph, Graham Candler, Michael Wright, Hans Hornung, and Ivett Leyva. "High enthalpy double-wedge experiments." In Advanced Measurement and Ground Testing Conference. American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-2238.

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Hatzl, Stefan, Tobias Sander, and Christian Mundt. "Experimental High Enthalpy Flow Characterization by Comparing Raman Spectroscopy and Enthalpy Balance." In 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-7302.

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Auweter-Kurtz, Monika, Harald Habiger, Thomas Wegmann, Monika Auweter-Kurtz, Harald Habiger, and Thomas Wegmann. "Diagnostics of high enthalpy plasma flows." In 32nd Thermophysics Conference. American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-2495.

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Mallinson, S., S. Gai, and N. Mudford. "High enthalpy, hypersonic compression corner flow." In 33rd Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-155.

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MILOS, FRANK. "ARCFLO analysis for high-enthalpy arc heaters." In 26th Thermophysics Conference. American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-1384.

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Matsui, Makoto, Kimiya Komurasaki, and Yoshihiro Arakawa. "Laser Absorption Spectroscopy in High Enthalpy Flows." In 38th AIAA Thermophysics Conference. American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-5325.

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EITELBERG, G., T. MCINTYRE, W. BECK, and J. LACEY. "The high enthalpy shock tunnel in Goettingen." In 28th Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-3942.

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Scortecci, Fabrizio, Fabrizio Paganucci, Luca d'Agostino, et al. "A new hypersonic high enthalpy wind tunnel." In 33rd Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-3017.

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Reports on the topic "High Enthalpy"

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Candler, Graham V., and Ioannis Nompelis. Code Validation Studies of High-Enthalpy Flows. Defense Technical Information Center, 2006. http://dx.doi.org/10.21236/ada470282.

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CALIFORNIA INST OF TECH PASADENA. Experimental Simulation and Diagnostics of High-Enthalpy Real-Gas Flows. Defense Technical Information Center, 1990. http://dx.doi.org/10.21236/ada229217.

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Rich, J. W., Walter R. Lempert, and Igor V. Adamovich. Energy Transfer Processes Among Electrons and Vibrationally Excited Air Species in High Enthalpy Flows. Defense Technical Information Center, 2007. http://dx.doi.org/10.21236/ada478735.

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Wannamaker, Philip E., James E. Faulds, and Burton Mack Kennedy. Integrating Magnetotellurics, Soil Gas Geochemistry and Structural Analysis to Identify Hidden, High Enthalpy, Extensional Geothermal Systems. Office of Scientific and Technical Information (OSTI), 2017. http://dx.doi.org/10.2172/1457571.

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Tasker, I. R., P. A. G. O`Hare, B. M. Lewis, G. K. Johnson, and E. H. P. Cordfunke. Thermochemistry of uranium compounds: XVI, Calorimetric determination of the standard molar enthalpy of formation at 298.15 K, low-temperature heat capacity, and high-temperature enthalpy increments of UO{sub 2}(OH){sub 2} {center_dot} H{sub 2}O (schoepite). Office of Scientific and Technical Information (OSTI), 1987. http://dx.doi.org/10.2172/60467.

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