Relevant bibliographies by topics / Cold flows

Contents

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

Academic literature on the topic 'Cold flows'

Author: Grafiati
Published: 4 June 2021
Last updated: 3 February 2022

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Journal articles on the topic "Cold flows"

1

Weitzner, H., A. Fruchtman, and P. Amendt. "Cold relativistic helically symmetric steady flows." Physics of Fluids 30, no. 2 (1987): 539. http://dx.doi.org/10.1063/1.866351.

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Natarajan, Aravind. "Caustics, Cold Flows, and Annual Modulation." Advances in Astronomy 2011 (2011): 1–11. http://dx.doi.org/10.1155/2011/285346.

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We discuss the formation of dark matter caustics, and their possible detection by future dark matter experiments. The annual modulation expected in the recoil rate measured by a dark matter detector is discussed. We consider the example of dark matter particles with a Maxwell-Boltzmann velocity distribution modified by a cold stream due to a nearby caustic. It is shown that the effect of the caustic flow is potentially detectable, even when the density enhancement due to the caustic is small. This makes the annual modulation effect an excellent probe of inner caustics. We also show that the phase of the annual modulation at low recoil energies does not constrain the particle mass unless the velocity distribution of particles in the solar neighborhood is known.
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Di Matteo, T., N. Khandai, C. DeGraf, Y. Feng, R. A. C. Croft, J. Lopez, and V. Springel. "COLD FLOWS AND THE FIRST QUASARS." Astrophysical Journal 745, no. 2 (January 12, 2012): L29. http://dx.doi.org/10.1088/2041-8205/745/2/l29.

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Claessens, Stijn, Michael P. Dooley, and Andrew Warner. "Portfolio Capital Flows: Hot or Cold?" World Bank Economic Review 9, no. 1 (1995): 153–74. http://dx.doi.org/10.1093/wber/9.1.153.

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Aragon-Calvo, M. A., J. Silk, and A. S. Szalay. "Locally cold flows from large-scale structure." Monthly Notices of the Royal Astronomical Society: Letters 415, no. 1 (June 7, 2011): L16—L20. http://dx.doi.org/10.1111/j.1745-3933.2011.01071.x.

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Voit, G. Mark, and Megan Donahue. "Problems with Cold Clouds and Cooling Flows." Astrophysical Journal 452 (October 1995): 164. http://dx.doi.org/10.1086/176288.

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Van Santen, Helmar, Chris R. Kleijn, and Harry E. A. Van Den Akker. "On turbulent flows in cold-wall CVD reactors." Journal of Crystal Growth 212, no. 1-2 (January 2000): 299–310. http://dx.doi.org/10.1016/s0022-0248(00)00033-6.

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Kimm, Taysun, Adrianne Slyz, Julien Devriendt, and Christophe Pichon. "Are cold flows detectable with metal absorption lines?" Monthly Notices of the Royal Astronomical Society: Letters 413, no. 1 (March 21, 2011): L51—L55. http://dx.doi.org/10.1111/j.1745-3933.2011.01031.x.

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Daines, S. J., A. C. Fabian, and P. A. Thomas. "The properties of cold clouds in cooling flows." Monthly Notices of the Royal Astronomical Society 268, no. 4 (June 15, 1994): 1060–72. http://dx.doi.org/10.1093/mnras/268.4.1060.

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Gross, A., and C. Weiland. "Numerical Simulation of Separated Cold Gas Nozzle Flows." Journal of Propulsion and Power 20, no. 3 (May 2004): 509–19. http://dx.doi.org/10.2514/1.2714.

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Dissertations / Theses on the topic "Cold flows"

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Daines, Stuart. "Cooling flows and cold gas in clusters of galaxies." Thesis, University of Cambridge, 1994. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.321020.

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Sebastião, Israel Borges. "Numerical simulation of MEMS-based cold gas micronozzle flows." Instituto Nacional de Pesquisas Espaciais, 2011. http://urlib.net/sid.inpe.br/mtc-m19/2011/08.11.13.08.

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A atual tendência no projeto de sistemas espaciais tem caminhado no sentido de se reduzir o custo do ciclo de vida dos programas através da redução da complexidade das missões dos satélites. Nesse contexto, umas das opções diz respetio à redução da massa total do sistema. Desse modo, conceitos de micropropulsão baseados em microtecnologias têm sido desenvolvidos a fim de se atender as exigências das futuras missões espaciais. O atual estágio da tecnologia de semicondutores à base de silício tem permitido a fabricação de sistemas de pequena escala, denominados por MEMS(MicroElectroMechanical Systems). Dentre as várias aplicações dos MEMS encontram-se os micropropulsores de baixo empuxo, onde os microbocais estão presentes. De acordo com a literatura relevante, a maioria dos estudos investigou o desempenho dos microbocais para diferentes escalas e condições de contorno. Entretanto, essas investigações não focaram na influência da curvatura da superfície na estrutura do escoamento em microbocais. É sabido que, em macrobocais, descontinuidades na curvatura alteram o desempenho dos bocais devido ao surgimento de ondas de choque no interior do dispositivo. Assim, com o intuito de adquirir uma compreensão mais profunda da física presente no escoamento em microbocais, a simulação numérica de um escoamento rarefeito num microbocal do tipo convergente-divergente é realizada através do Método de Simulção Direta de Monte Carlo (DSMC). Tal dispositivo é considerado como parte de uma matriz de microbocais. Considerando ainda uma superfície divergente do tipo convexa-côncava, os impactos de diferentes perfis dessa superfície na estrutura do escoamento, quantidades aerodinâmicas da superfície e desempenho do microbocal são explorados alterando-se a inclinação e o raio de curvatura da superfície no ponto de inflexão. Com o propósito de se desacoplar outros efeitos geométricos, a razão entre as áreas da garganta e de saída assim como o ângulo de divergência na saída são mantidos os mesmos para todos os casos. Além disso, as condições de entrada e saída são baseadas em valores pré-definidos de pressão. Os resultados computacionais apontaram um pequeno impacto nas propriedades macroscópicas devido às variações na inclinação e curvatura da superfície divergente. As hipóteses de simetria adotadas neste trabalho resultaram numa região de recirculação no escoamento externo. As simulações ainda mostraram que o não-equilíbrio termodinâmico ocorre em todo escoamento divergente, em especial, no lábio do bocal. No que diz respeito às quantidades aerodinâmicas, as simulações indicaram que as cargas térmicas e mecânicas que agem ao longo da superfície divergente dependem fortemente da inclinação da superfície próximo ao ponto de inflexão. Finalmente, este estudo ainda revelou que a forma geométrica da superfície divergente não desempenhou uma influência significativa no impulso específico. De qualquer modo, a presença da superfície divergente forneceu um impulso específico que é cerca de duas vezes maior que aquele obtido para um microbocal apenas com a parte convergente operando nas mesmas condições.
The recent tendency in the design of space systems has aligned to reduce the life cycle cost of space programs by means of a reduction in the complexity of satellite missions. In this context, one of the possible options is reducing the mass of the whole system. Therefore, concepts of micropropulsion based on microtechnologies have been developed in order to attend the requirements of future space missions. The current state of semiconductor technology based on silicon has allowed the manufacturing process of small scale systems, called as MEMS (MicroElectroMechanical Systems). Among the many MEMS applications are the microunits of low thrust, where micronozzles are present. According to the relevant literature, the most studies investigated the micronozzle performance for different length scales and flow conditions. However, these investigations have not focused on the influence of the surface curvature on the micronozzle flow structure. In macronozzles, it is know that discontinuities on the surface affect the system performance due to the arising of shock waves inside the device. Thus, in order to obtain further insight into the physics of micronozzle flows, a numerical simulation of a rarefied flow in a convergent-divergent micronozzle array with rectangular cross-section is investigated by using the Direct Simulation Monte Carlo~(DSMC) method. By considering a convex-concave divergent surface, the impact of different divergent shapes on the two-dimensional flowfield structure, aerodynamic surface quantities and micronozzle performance are explored by changing the surface slope and radius of curvature at the inflection point. In order to decouple other geometric influences, the ratio between exit and throat areas as well as the divergent exit angle were kept the same for all cases. Moreover, the inlet-outlet boundary conditions are based on pre-defined pressure values. The computational results pointed out a small impact on the macroscopic properties due to variations in the slope and curvature of the divergent surface. The symmetric assumptions employed in this account resulted in a recirculation region in the external flow. The simulations also showed that thermodynamic nonequilibrium takes place in the entire divergent flow, in special, at the nozzle lip. By concerning to the aerodynamic surface quantities, simulations indicated that the thermal and mechanical loads that take place along the divergent surface are highly dependent on the smoothness of the surface along the inflection point. Finally, this study also revealed that the geometric shape of the divergent surface does not perform significant influence on the specific impulse. Anyway, the presence of the divergent surface provided a specific impulse that is almost two times higher than that one obtained by a micronozzle with only the convergent part operating in the same conditions.
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Burns, Paul. "Interactions between downslope flows and a developing cold-air pool." Thesis, University of Hertfordshire, 2015. http://hdl.handle.net/2299/15500.

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Downslope flows and regions of enhanced cooling have important impacts on society and the environment. Parameterisation of these often subgrid-scale phenomena in numerical models requires a sound understanding of the underlying physical processes, which has been the overarching aim of this work. A numerical model has been used to characterise the development of a region of enhanced cooling in an idealised alpine valley with width and depth of order 10 and 1 km, respectively, under stable, decoupled, poorly-drained conditions. A focus of this work has been to remove the uncertainty surrounding the forcing mechanisms behind the development of regions of enhanced cooling. The average valley-atmosphere cooling has been found to be almost equally partitioned between radiative and dynamics effects. Complex interactions between the downslope flows and the region of enhanced cooling have been quantified for the first time. For example, relatively large variations in the downslope flows are generally restricted to the region of enhanced cooling and cannot solely be attributed to the analytical model of [McNider, 1982a]. These flow variations generally coincide with return flows above the downslope flows, where a thin region of unstable air occurs, as well as coinciding with elongated downslope flow structures. The impact of these interactions on the dispersion of passive pollutants has been investigated. For example, pollutants are generally trapped within the region of enhanced cooling. The concentration of pollutants within the region of enhanced cooling, emitted over the lower half of the slopes, increase as the emission source moves away from the ground-based inversion that expands from the bottom of the valley. The concentration of pollutants within the region of enhanced cooling is very similar when varying the location of the emission source over the top half of the valley slopes. This work includes a test of the effects of varying the horizontal numerical grid resolution on average valley-atmosphere temperature changes.
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Bardot, Leon. "Explosive volcanism on Santorini : palaeomagnetic estimation of emplacement temperatures of pyroclastics." Thesis, University of Oxford, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.360162.

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Laurantzon, Fredrik. "Flow Measuring Techniques in Steady and Pulsating Compressible Flows." Licentiate thesis, KTH, Mekanik, 2010. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-26344.

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This thesis deals with flow measuring techniques applied on steady and pulsatingflows. Specifically, it is focused on gas flows where density changes canbe significant, i.e. compressible flows. In such flows only the mass flow ratehas a significance and not the volume flow rate since the latter depends onthe pressure. The motivation for the present study is found in the use of flowmeters for various purposes in the gas exchange system for internal combustionengines. Applications can be found for instance regarding measurements of airflow to the engine, or measurements of the amount of exhaust gas recirculation.However the scope of thesis is wider than this, since the thesis aims toinvestigate the response of flow meters to pulsating flows. The study is mainlyexperimental, but it also includes an introduction and discussion of several inindustry, common flow measuring techniques.The flow meters were studied using a newly developed flow rig, designedfor measurement of steady and pulsating air flow of mass flow rates and pulsefrequencies typically found in the gas exchange system of cars and smallertrucks. Flow rates are up to about 200 g/s and pulsation frequencies from 0 Hz(i.e. steady flow) up to 80 Hz. The study included the following flow meters:hot-film mass flow meter, venturi flowmeter, Pitot tube, vortex flowmeter andturbine flowmeter. The performance of these meters were evaluated at bothsteady and pulsating conditions. Furthermore, the flow under both steady andpulsating conditions were characterized by means of a resistance-wire basedmass flow meter, with the ability to perform time resolved measurements ofboth the mass flux ρu, and the stagnation temperature T0.Experiments shows that, for certain flow meters, a quasi-steady assumptionis fairly well justified at pulsating flow conditions. This means that thefundamental equations describing the steady flow, for each instant of time,is applicable also in the pulsating flow. In the set-up, back-flow occurred atcertain pulse frequencies, which can result in highly inaccurate output fromcertain flow meters, depending on the measurement principle. For the purposeof finding means to determine when back flow prevails, LDV measurementswere also carried out. These measurements were compared with measurementsusing a vortex flow meter together with a new signal processing technique basedon wavelet analysis. The comparison showed that this technique may have apotential to measure pulsating flow rates accurately.Descriptors: Flow measuring, compressible flow, steady flow, pulsating flow,hot-wire anemometry, cold-wire anemometry.
QC 20101208
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Nanson, Richard A. "Navier/Stokes/Direct simulation Monte Carlo modeling of small cold gas thruster nozzle and plume flows." Link to electronic thesis, 2002. http://www.wpi.edu/Pubs/ETD/Available/etd-0424102-132343.

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Nanson, III Richard A. "Navier/Stokes/Direct Simulation Monte Carlo Modeling of Small Cold Gas Thruster Nozzle and Plume Flows." Digital WPI, 2002. https://digitalcommons.wpi.edu/etd-theses/254.

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This study involves the modeling of small cold-gas (N2) thrusters nozzle and plume flows, their interactions with spacecraft surfaces and the induced pressure environment. These small cold-gas thrusters were used for pitch, yaw and roll control and were mounted on the bottom of the conical Environmental Monitor Payload (EMP) suborbital spacecraft. The pitch and yaw thrusters had 0.906 mm throat diameter and 4.826 mm exit diameter, while the roll thrusters had 1.6 mm throat diameter and 5.882 mm exit diameter. During thruster firing, at altitudes between 670 km and 1200 km, pressure measurements exhibited non-periodic pulses (Gatsonis et al., 1999). The pressure sensor was located inside the EMP and was connected to it's sidewall with a 0.1-m long, 0.022-m diameter tube and the pressure pulses appeared instantaneously with the firings for thrusters without a direct line-of-sight with the sensor entrance. Preliminary analysis showed that the plume of these small EMP thrusters undergoes transition from continuous to rarefied. Therefore, nozzle and plume simulations are performed using a combination of Navier-Stokes and Direct Simulation Monte Carlo codes. This study presents first a validation of the Navier-Stokes code Rampant used for the continuous EMP nozzle and plume simulations. The first Rampant validation example involves a two-dimensional axisymetric freejet expansion and is used to demonstrate the use of Bird's breakdown parameter. Results are compared favorably with those of Bird (1980) obtained through the method of characteristics. The second validation example involves three-dimensional plume simulations of a NASA thruster. This nitrogen nozzle has a throat diameter of 3.18 mm, an exit diameter of 31.8 mm, half-angle of 20 degrees, stagnation temperature of 699 K, stagnation pressure of 6,400 Pa. Simulation results are compared favorably with previous Navier-Stokes and Direct Simulation Monte Carlo numerical work. The third validation example involves three-dimensional simulations of Rothe's (1970) nozzle that has a throat diameter of 2.5 mm, an exit diameter of 20.3 mm, half-angle of 20 degrees, operating at stagnation temperature of 300 K and pressure of 1975 Pa. Numerical results also compared favorably to experimental data. The combined Navier-Stokes/DSMC approach and the EMP simulation results are presented and discussed. The continuous part of the EMP nozzle and plume flow is modeled using the three-dimensional Navier-Stokes Rampant code. The Navier-Stokes domain includes the geometry of the nozzle and the EMP base until transition of the continuous flow established by Bird's breakdown parameter. The rarefied part of the plume flow is modeled using the Direct Simulation Monte Carlo code DAC. Flowfield data obtained inside the breakdown surface from the Navier-Stokes simulation are used as inputs to the DSMC simulations. The DSMC domain includes the input surface and the EMP spacecraft geometry. The combined Navier-Stokes/DSMC simulations show the complex structure of the plume flow as it expands over the EMP surfaces. Plume reflection and backflow are demonstrated. The study also summarizes findings presented by Gatsonis et al. (2000), where the DSMC predictions at the entrance of the pressure sensor are used as inputs to a semi-analytical model to predict the pressure inside the sensor. It is shown that the pressure predictions for the pitch/yaw thrusters are close to the measurements. The plume of a pitch or yaw thruster reaches the pressure sensor after expanding on the EMP base. The pressure predicted for the roll thruster is larger that the measured. This is attributed to the uncertainty in the roll thruster location on the EMP base resulting, in the simulation, in a component of direct flow to the sensor.
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Kalpakli, Athanasia. "Experimental study of turbulent flows through pipe bends." Licentiate thesis, KTH, Linné Flow Center, FLOW, 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-93316.

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This thesis deals with turbulent flows in 90 degree curved pipes of circular cross-section. The flow cases investigated experimentally are turbulent flow with and without an additional motion, swirling or pulsating, superposed on the primary flow. The aim is to investigate these complex flows in detail both in terms of statistical quantities as well as vortical structures that are apparent when curvature is present. Such a flow field can contain strong secondary flow in a plane normal to the main flow direction as well as reverse flow. The motivation of the study has mainly been the presence of highly pulsating turbulent flow through complex geometries, including sharp bends, in the gas exchange system of Internal Combustion Engines (ICE). On the other hand, the industrial relevance and importance of the other type of flows were not underestimated. The geometry used was curved pipes of different curvature ratios, mounted at the exit of straight pipe sections which constituted the inflow conditions. Two experimental set ups have been used. In the first one, fully developed turbulent flow with a well defined inflow condition was fed into the pipe bend. A swirling motion could be applied in order to study the interaction between the swirl and the secondary flow induced by the bend itself. In the second set up a highly pulsating flow (up to 40 Hz) was achieved by rotating a valve located at a short distance upstream from the measurement site. In this case engine-like conditions were examined, where the turbulent flow into the bend is non-developed and the pipe bend is sharp. In addition to flow measurements, the effect of non-ideal flow conditions on the performance of a turbocharger was investigated. Three different experimental techniques were employed to study the flow field. Time-resolved stereoscopic particle image velocimetry was used in order to visualize but also quantify the secondary motions at different downstream stations from the pipe bend while combined hot-/cold-wire anemometry was used for statistical analysis. Laser Doppler velocimetry was mainly employed for validation of the aforementioned experimental methods. The three-dimensional flow field depicting varying vortical patterns has been captured under turbulent steady, swirling and pulsating flow conditions, for parameter values for which experimental evidence has been missing in literature.
QC 20120425
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Örlü, Ramis. "Experimental study of passive scalar mixing in swirling jet flows." Licentiate thesis, KTH, Mechanics, 2006. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-4142.

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Despite its importance in various industrial applications there is still a lack of experimental studies on the dynamic and thermal field of swirling jets in the near-field region. The present study is an attempt to close this lack and provide new insights on the effect of rotation on the turbulent mixing of a passive scalar, on turbulence (joint) statistics as well as the turbulence structure.

Swirl is known to increase the spreading of free turbulent jets and hence to entrain more ambient fluid. Contrary to previous experiments, which leave traces of the swirl generating method especially in the near-field, the swirl was imparted by discharging a slightly heated air flow from an axially rotating and thermally insulated pipe (6 m long, diameter 60 mm). This gives well-defined axisymmetric streamwise and azimuthal velocity distributions as well as a well-defined temperature profile at the jet outlet. The experiments were performed at a Reynolds number of 24000 and a swirl number (ratio between the angular velocity of the pipe wall and the bulk velocity in the pipe) of 0.5.

By means of a specially designed combined X-wire and cold-wire probe it was possible to simultaneously acquire the instantaneous axial and azimuthal velocity components as well as the temperature and compensate the former against temperature variations. The comparison of the swirling and non-swirling cases clearly indicates a modification of the turbulence structure to that effect that the swirling jet spreads and mixes faster than its non-swirling counterpart. It is also shown that the streamwise velocity and temperature fluctuations are highly correlated and that the addition of swirl drastically increases the streamwise passive scalar flux in the near field.

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Ben, Nasr Ouissem. "Numerical simulations of supersonic turbulent wall-bounded flows." Phd thesis, INSA de Rouen, 2012. http://tel.archives-ouvertes.fr/tel-01059805.

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This work deals with spatially-evolving supersonic turbulent boundary layers over adiabatic and cold walls at M∞ = 2 and up to Re0 ≈ 2600 using 3 different SGS models. The numerical methodology is based on high-order split-centered scheme to discretize the convective fluxes of the Navier-Stokes equations . For the adiabatic case, it is demonstrated that all SGS models require a comparable minimum grid-refinement in order to capture accurately the near-wall-turbulence. Overall, the models exhibit correct behavior when predictiong the dynamic properties, but show different performances for the temperature distribution in the near-wall region. For the isothermal case, it is found that the compressibility effects are not enhanced due to the wall cooling. As expected, the total temperature fluctuations are not negligible in the near-wall region. The study shows that the anti-correlation linking both velocity and temperature fields, derived from the Morkovin's hypothesis, is not satisfied.
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Books on the topic "Cold flows"

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Baysal, Oktay. Navier-Stokes analysis of cold scramjet-afterbody flows. Norfolk, Va: Dept. of Mechanical Engineering and Mechanics, College of Engineering and Technology, Old Dominion University, 1989.

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Baysal, Oktay. Navier-Stokes analysis of cold scramjet-afterbody flows. Norfolk, Va: Dept. of Mechanical Engineering and Mechanics, College of Engineering and Technology, Old Dominion University, 1989.

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Thompson, H. Doyle. Laser velocimeter measurements and analysis in turbulent flows with combustion: Part IV - Two-component cold-flow measurements. Wright-Patterson Air Force Base: Air Force Wright Aeronautical Laboratories, 1986.

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Tuomisto, H. Thermal mixing tests in a semiannular downcomer with interacting flows from cold legs. Washington, D.C: U.S. Nuclear Regulatory Commission, Office of Nuclear Regulatory Research, 1986.

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Canright, David. Thermocapillary flow near a cold wall. Monterey, Calif: Naval Postgraduate School, 1993.

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Seymour, M. J. Cold downdraughts: Application guide 2/91. Bracknell: Building Services Research and Information Association, 1992.

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S, Elleson James, and American Society of Heating, Refrigerating and Air-Conditioning Engineers., eds. Cold air distribution: System design guide. Atlanta, Ga: American Society of Heating, Refrigerating and Air-Conditioning Engineers, 1996.

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Baysal, Oktay. Viscous computations of cold air/air flow around scramjet nozzle afterbody. Hampton, Va: Langley Research Center, 1991.

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Huber, Michael R. An investigation of low Marangoni number fluid flow in a cold corner. Monterey, Calif: Naval Postgraduate School, 1993.

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O'Hern, William J. Noah John Rondeau's Adirondack wilderness days: A year with the hermit of Cold River Flow. Cleveland, N.Y: Forager Press, 2009.

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Book chapters on the topic "Cold flows"

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Tenenbaum, Alexander, and Eugenio Tabet. "Lattice Instability and Cold Fusion in Deuterated Metals." In Microscopic Simulations of Complex Flows, 323–27. Boston, MA: Springer US, 1990. http://dx.doi.org/10.1007/978-1-4684-1339-7_25.

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Jaffe, Walter, Malcolm Bremer, and Roderick Johnstone. "Warm Molecular Gas in AGNS and Cooling Flows." In Cold Gas at High Redshift, 195–97. Dordrecht: Springer Netherlands, 1996. http://dx.doi.org/10.1007/978-94-009-1726-2_19.

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Kordulla, W., J. Periaux, and T. Alziary de Roquefort. "Attempt to Evaluate the Computations for Test Case 6.1 - Cold Hypersonic Flow Past Ellipsoidal Shapes -." In Hypersonic Flows for Reentry Problems, 689–712. Berlin, Heidelberg: Springer Berlin Heidelberg, 1991. http://dx.doi.org/10.1007/978-3-642-76527-8_46.

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Knapp, G. R. "Hot and Cold Gas in Early-Type Galaxies: A Comparison of X-Ray, HI and Far Infrared Emission." In Cooling Flows in Clusters and Galaxies, 93–102. Dordrecht: Springer Netherlands, 1988. http://dx.doi.org/10.1007/978-94-009-2953-1_10.

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Hirahara, Masafumi, Kanako Seki, and Toshifumi Mukai. "Cold Dense Ion Flows in the Distant Magnetotail: The Geotail Results." In New Perspectives on the Earth's Magnetotail, 45–60. Washington, D. C.: American Geophysical Union, 2013. http://dx.doi.org/10.1029/gm105p0045.

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Giovannini, A. "Dyanmics of Cold and Reacting Flows on Backward Facing Step Geometry." In Lecture Notes in Engineering, 694–714. New York, NY: Springer US, 1989. http://dx.doi.org/10.1007/978-1-4613-9631-4_32.

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Schumann, Jan-Erik, Markus Fertig, Volker Hannemann, Thino Eggers, and Klaus Hannemann. "Numerical Investigation of Space Launch Vehicle Base Flows with Hot Plumes." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 179–91. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_11.

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Abstract The flow field around generic space launch vehicles with hot exhaust plumes is investigated numerically. Reynolds-Averaged Navier-Stokes (RANS) simulations are thermally coupled to a structure solver to allow determination of heat fluxes into and temperatures in the model structure. The obtained wall temperatures are used to accurately investigate the mechanical and thermal loads using Improved Delayed Detached Eddy Simulations (IDDES) as well as RANS. The investigated configurations feature cases both with cold air and hot hydrogen/ water vapour plumes as well as cold and hot wall temperatures. It is found that the presence of a hot plume increases the size of the recirculation region and changes the pressure distribution on the nozzle structure and thus the loads experienced by the vehicle. The same effect is observed when increasing the wall temperatures. Both RANS and IDDES approaches predict the qualitative changes between the configurations, but the reattachment location predicted by IDDES is up to 7% further upstream than that predicted by RANS. Additionally, the heat flux distribution along the nozzle and base surface is analysed and shows significant discrepancies between RANS and IDDES, especially on the nozzle surface and in the base corner.
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Gooch, Jan W. "Cold Flow." In Encyclopedic Dictionary of Polymers, 152. New York, NY: Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4419-6247-8_2564.

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Kirchheck, Daniel, Dominik Saile, and Ali Gülhan. "Rocket Wake Flow Interaction Testing in the Hot Plume Testing Facility (HPTF) Cologne." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 145–62. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_9.

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Abstract Rocket wake flows were under investigation within the Collaborative Research Centre SFB/TRR40 since the year 2009. The current paper summarizes the work conducted during its third and final funding period from 2017 to 2020. During that phase, focus was laid on establishing a new test environment at the German Aerospace Center (DLR) Cologne in order to improve the similarity of experimental rocket wake flow–jet interaction testing by utilizing hydrogen–oxygen combustion implemented into the wind tunnel model. The new facility was characterized during tests with the rocket combustor model HOC1 in static environment. The tests were conducted under relevant operating conditions to demonstrate the design’s suitability. During the first wind tunnel tests, interaction of subsonic ambient flow at Mach 0.8 with a hot exhaust jet of approx. 920 K was compared to previously investigated cold plume interaction tests using pressurized air at ambient temperature. The comparison revealed significant differences in the dynamic response of the wake flow field on the different types of exhaust plume simulation.
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Hartel, Richard W., and AnnaKate Hartel. "Caramel Cold Flow." In Candy Bites, 119–22. New York, NY: Springer New York, 2014. http://dx.doi.org/10.1007/978-1-4614-9383-9_30.

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Conference papers on the topic "Cold flows"

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Zhang, Yibin, Steven J. Beresh, Katya M. Casper, Daniel R. Richardson, Melissa Soehnel, and Russell Spillers. "Tailoring FLEET for Cold Hypersonic Flows." In AIAA Scitech 2020 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-1020.

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SIKIVIE, P. "COLD DARK MATTER FLOWS AND CAUSTICS." In Proceedings of the 10th International Symposium. World Scientific Publishing Company, 2005. http://dx.doi.org/10.1142/9789812701756_0014.

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SIKIVIE, P. "COLD DARK MATTER FLOWS AND CAUSTICS." In Proceedings of the Fifth International Workshop. WORLD SCIENTIFIC, 2005. http://dx.doi.org/10.1142/9789812701848_0011.

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Ivanov, M., G. Markelov, A. Ketsdever, and D. Wadsworth. "Numerical study of cold gas micronozzle flows." In 37th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-166.

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Zhang, Yibin, Steven J. Beresh, Katya M. Casper, Daniel R. Richardson, Melissa Soehnel, and Russell Spillers. "Correction: Tailoring FLEET for Cold Hypersonic Flows." In AIAA Scitech 2020 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-1020.c1.

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Gosman, A. David. "Multidimensional Modelling of Cold Flows and Turbulence in Reciprocating Engines." In SAE International Congress and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1985. http://dx.doi.org/10.4271/850344.

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Palm, P., R. Meyer, A. Bezant, I. Adamovich, J. Rich, and S. Gogineni. "Feasibility study of MHD control of cold supersonic plasma flows." In 40th AIAA Aerospace Sciences Meeting & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-636.

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Gaeta, Jr., R., K. Ahuja, R. Gaeta, Jr., and K. Ahuja. "A unique flow-duct facility to measure liner performance in cold and heated flows." In 3rd AIAA/CEAS Aeroacoustics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-1700.

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Merriman, Samuel, Elke Ploenjes, Peter Palm, and Igor Adamovich. "Shock wave control by nonequilibrium plasmas in cold supersonic gas flows." In Fluids 2000 Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-2327.

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Gatsonis, Nikolaos A., and Sergey AVerkin. "Simulation of Cold Nitrogen Flows in Nanonozzles with Atmospheric Inlet Pressures." In 44th AIAA Fluid Dynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-2635.

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Reports on the topic "Cold flows"

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Ivanov, M. S., G. N. Markelov, A. D. Ketsdever, and D. C. Wadsworth. Numerical Study of Cold Gas Micronozzle Flows. Fort Belvoir, VA: Defense Technical Information Center, January 1999. http://dx.doi.org/10.21236/ada386960.

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Simoneau, J. P., H. Noe, and B. Menant. Large eddy simulation of mixing between hot and cold sodium flows - comparison with experiments. Office of Scientific and Technical Information (OSTI), September 1995. http://dx.doi.org/10.2172/107780.

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Tuomisto, H., and P. Mustonen. Thermal mixing tests in a semiannular downcomer with interacting flows from cold legs: International Agreement Report. Office of Scientific and Technical Information (OSTI), October 1986. http://dx.doi.org/10.2172/7089518.

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Kline, Adam, and Tim Hwang. From Cold War Sanctions to Weaponized Interdependence: An Annotated Bibliography on Competition and Control over Emerging Technologies. Center for Security and Emerging Technology, September 2021. http://dx.doi.org/10.51593/20210027.

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As U.S. policymakers grapple with the need to control international technology flows, this annotated bibliography distills key lessons and surveys 50 years of scholarship, government documents, and commentary. The resources it presents are at the intersection of international economics and technology and span from the Cold War to the current challenges surrounding U.S.-China relations.
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Famouri, Parviz. Cold-Flow Circulating Fluidized-Bed Identification. Office of Scientific and Technical Information (OSTI), July 2005. http://dx.doi.org/10.2172/910283.

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AIR FORCE RESEARCH LAB EDWARDS AFB CA. Integrated Powerhead Demonstration's Oxidizer Turbopump Cold Flow Tests Completed. Fort Belvoir, VA: Defense Technical Information Center, May 2002. http://dx.doi.org/10.21236/ada410057.

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Ayoul-Guilmard, Q., S. Ganesh, M. Nuñez, R. Tosi, F. Nobile, R. Rossi, and C. Soriano. D5.3 Report on theoretical work to allow the use of MLMC with adaptive mesh refinement. Scipedia, 2021. http://dx.doi.org/10.23967/exaqute.2021.2.002.

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This documents describes several studies undertaken to assess the applicability of MultiLevel Monte Carlo (MLMC) methods to problems of interest; namely in turbulent fluid flow over civil engineering structures. Several numerical experiments are presented wherein the convergence of quantities of interest with mesh parameters are studied at different Reynolds’ numbers and geometries. It was found that MLMC methods could be used successfully for low Reynolds’ number flows when combined with appropriate Adaptive Mesh Refinement (AMR) strategies. However, the hypotheses for optimal MLMC performance were found to not be satisfied at higher turbulent Reynolds’ numbers despite the use of AMR strategies. Recommendations are made for future research directions based on these studies. A tentative outline for an MLMC algorithm with adapted meshes is made, as well as recommendations for alternatives to MLMC methods for cases where the underlying assumptions for optimal MLMC performance are not satisfied.
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Cloutman, L. D. Numerical simulation of cold flow patterns and turbulent mixing in a simplified burner. Office of Scientific and Technical Information (OSTI), October 1994. http://dx.doi.org/10.2172/113879.

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Strickland, J. H. Modeling of a sinusoidal lobed injector: Vorticity and concentration fields for a cold flow. Office of Scientific and Technical Information (OSTI), December 1995. http://dx.doi.org/10.2172/204112.

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Nieh, S. Development of a vortexing combustor (VC) for space/water heating applications (cold flow modeling). Office of Scientific and Technical Information (OSTI), August 1988. http://dx.doi.org/10.2172/6858688.

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