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We have tried to extend the short-ranged radial distribution function of the molecular dynamics (MD) simulation for a monatomic Lennard-Jones solvent by applying the Ornstein–Zernike theory with two hybrid closures. One was the hybrid with the Kovalenko–Hirata or the KH closure (hybrid MD–KH closure), whereas the other was the hybrid with the Kobryn–Gusarov–Kovalenko or the KGK closure (hybrid MD–KGK closure). As long as the switching distance between the MD and the KH (or the KGK) is chosen appropriately, the direct correlation functions obtained by these hybrid closures were almost identical to each other, which also agree with those of the hybrid closure with the hypernetted chain or the HNC (hybrid MD–HNC closure). The calculations on the solute–solvent correlation function and the solvation free energy also supported the practical equivalence among the hybrid MD–KH, hybrid MD–KGK, and hybrid MD–HNC closures.

Acoustic simulation of hot jets issuing from a rectangular hypersonic nozzle was carried out. The aim of this study is, even though qualitative to some extent, to establish a method capable of predicting the acoustic characteristics of the high-temperature and high-velocity jets issuing from the realistic hypersonic nozzle having a complicated geometry. Two kinds of test nozzles, 2.4% scaled model with afterburner for hot jet experiments and 1.0% scaled model for cold-air/helium mixture jet experiments, were manufactured and tested. By using a high-enthalpy wind-tunnel plant, acoustic characteristics of the hot jets issuing from the rectangular hypersonic nozzle for several representative but realistic high-temperature and high-velocity jet conditions were obtained. At the same time, by using a small anechoic chamber, the acoustic characteristics of the hot jets were duplicated using cold-air/helium mixture jets having the same velocities. Although we have to pay attention to some noted exceptions, the di...

Mean-flow and acoustic characteristics of cold-air jets issuing from a rectangular hypersonic nozzle were investigated experimentally. The final goal of this study is (even though qualitative to some extent) to establish a method capable of predicting the acoustic characteristics of the high-temperature and high-velocity jets issuing from a hypersonic engine. As the first step, a high-enthalpy wind-tunnel plant without anechoic treatment was used for the cold-air jet experiments, and the acoustic data obtained were compared with those obtained in a small anechoic chamber. It is shown that, while it is necessary to pay attention to some noted exceptions, the directivity patterns and spectral shapes agree well at a wide range of radiation angles by taking into account the correction of −2.5 dB. The mean-flow measurements revealed that, due to the complicated geometry of the nozzle, the jet has a highly asymmetric velocity profile at the ramp end and that the development of the jet plume is also inclined an...

Combustion characteristics of liquid hydrocarbon fuels are studied in a model combustor of SCRAM jet engines. The Mach number and total pressure of main flow in the combustor are 2.0 and 0.38 MPa, respectively, and the total temperature is varied from 1800 to 2400 K. Five kinds of n-alkane fuels such as n-heptane, n-octane, n-decane, n-tridecane and n-hexadecane are employed in experiments. Fuels are injected with a carrier nitrogen gas perpendicular to the mail flow in the combustor and the self-ignition behavior is investigated. The results show that the liquid fuels with lower carbon number have better self-ignition performance. This suggests that physical properties of liquid fuels such as volatility have a dominant effect on the self-ignition. The flame-holding behavior is investigated with the addition of pilot hydrogen to carrier nitrogen gas. The critical equivalence ratio at which the stable combustion keeps after cut-off of the pilot hydrogen is obtained. The relationship between the critical equivalence ratio and carbon number of fuel shows that fuels with the carbon numbers from 8 to 10 have the best flame-holding performance among the tested fuels. These experimental results can be expressed qualitatively by the simplified analysis with the concept of physical and chemical induction times.

Flame is affected by an external electric field because it contains ions and electrons related to chemical reactions. On the other hand, the movement of ions and electrons affects the external electric field due to their charge. This paper reports the combustion experiments of ethanol droplets in vertical electric field with variable distance electrodes apparatus in order to discuss the change of the external electric field due to the existence of flame. From a one-dimensional steady-state analysis, if the electric field is changed spatially, its effect on combustion behavior is aligned with V 2 / L 3 and not V / L, where V is the applied voltage between electrodes, and L is distance between the electrodes. The droplet is burned between the two horizontal parallel electrodes. The flame deformation and the electric current are characterized by various electrode distances, and respectively, applied voltages. The vertical electric field induces a body force downwards on the flame. The flame deforms downward in the electric field because the electric body force counters the natural buoyancy. The relation between the applied voltage and electrode distance is investigated when the flame becomes vertically symmetrical and the results show that the deformation is the function of V / L 1.5 . This indicates that the change in the electric field should be considered to discuss the effect of an external electric field on combustion behavior. The experimental results are rearranged using e V 2 / L 3 where e is electric permittivity of air because its unit is N/m 3 and it considered to be the representative electric body force. Although its application is limited, qualitatively it can help to explain the experimental results of a droplet combustion. In addition, the degree of electron attachment to neutral molecules is discussed to interpret our experimental results.

Flames are affected by external electric fields because they contain ions and electrons. The movement of ions and electrons affects the external electric field owing to their charge. In this context, this paper discusses the change in the electric field on the basis of experimental results obtained at different electrode distances. Employing one-dimensional (1D) steady-state analysis, we assume that if the electric field is changed spatially, the effect of the electric field on combustion behavior is aligned with V2/L3, where V is the applied voltage between the electrodes and L is the distance between the electrodes. Because a flame deforms to a cathode owing to electric body force in an electric field, the change in the flame shape of burning ethanol droplets observed in a vertical DC electric field and the electric current during combustion are measured as flame characteristics. The results reveal that applied electric voltage exists where the flame becomes vertically symmetrical to balance the buoyancy due to the electric body force. The relationship between m and n of Vm/Ln for flame symmetry is around n/m = 1.5. On the basis of these results, all experimental results for different electrode distances are rearranged with eV2/L3, which is a representative electric body force, and it is proved that the use of parameter eV2/L is effective. These results indicate that the change in the electric field due to the existence of a flame should be considered when examining the effect of an external electric field on combustion behavior.

Effects of nozzle scale, total temperature, and an afterburner on jet noise characteristics from a pre-cooled turbojet engine are investigated experimentally. In JAXA (Japan Aerospace Exploration Agency), a pre-cooled turbojet engine for an HST (Hypersonic transport) is under development. In the present study, 1.0%- and 2.4%-scaled models of the rectangular plug nozzle (Nozzles I and II) are manufactured, and the jet noise characteristics are investigated under a wide range of total temperatures. For Nozzle I, no air-heater is utilized and the total temperature is 290K. For Nozzle II, a pebble heater and an afterburner (AB) are utilized upstream of the nozzle model, and the total temperature is varied from 520K (pebble heater) to 1540K (pebble heater + AB). The total pressure is set at 0.27 and 0.30MPa(a) for both nozzle models. Jet noise is measured using a high-frequency microphone set at 135 deg from the engine inlet, and normalized jet noise spectra are obtained based on AUjn law and Helmholtz number. For cases without afterburner, the normalized spectra agrees well regardless of the nozzle scale and total temperature where the velocity index lies from n = 7.7 to 9.2, and the correlation factor between the two facilities is shown to be about 1dB. For the case with afterburner, the normalized spectrum does not agree with other conditions where the velocity index n seems to be about 4.

Pre-cooled turbojet engine is investigated to realize Mach 5 class hypersonic transport aircraft. The engine has been demonstrated under sea level static and Mach 2 flight conditions using hydrogen as fuel. In this study, Mach 4 propulsion wind tunnel test is performed and the performance of air intake, pre-cooler, core engine and exhaust nozzle are obtained. Liquid nitrogen is supplied to the pre-cooler as a coolant in place of liquid hydrogen. Gaseous hydrogen is supplied to the main burner to drive the turbine with the combustion gas. A protective screen is placed in front of the pre-cooler to prevent damages of it from high-speed particles. Bypass door is placed in front of the core engine to start the mixed compression air intake at low speed operation of the core engine. As a result, the engine performance data is obtained without any damage of pre-cooler. Air intake is started by the effect of bypass door at low speed operation of the core engine.

Surface diffusion during decay of a two-dimensional nano-island formed on Si(1 0 0) surface at 750–800 K is studied using STM and a kinetic Monte Carlo simulation. From a surface diffusion point of view, decay proceeds so that the total diffusion rate of atoms on a surface decreases. Atoms at step edges move more frequently than terrace atoms, which results in decay from step edges of the island. In addition, a terrace atom takes part in surface diffusion in the same way as an atom from steps of the island once it hops up on a terrace leaving a vacancy. The mass transport is not a specific atom process but terrace atoms and vacancies on the terrace are involved. Repeated upward and downward hops of atoms and their difference are combined with surface diffusion, which leads to the mass transport. Some tracks of atom using simulation show random walk with preferential diffusion along step edges, re-entering to the island, exchange of diffusing atom and filling in a vacancy on the terrace. The motion of the center of the island to the upper side of the terrace observed by STM is also well reproduced in the simulation.

A variety of benzylic alcohols were oxidized to the corresponding carbonyl compounds selectively with 30% hydrogen peroxide (H2O2) in the presence of activated carbon. Alkylarenes such as fluorenes, xanthenes, and anthrone were also effectively oxygenated to the corresponding carbonyl compounds with 30% H2O2 as oxidant in the presence of activated carbon.

Pre-cooled turbojet engine is investigated to realize Mach 5 class hypersonic transport aircraft. The engine has been demonstrated under sea level static and Mach 2 flight conditions using hydrogen as fuel. Presently, Mach 5 propulsion wind tunnel test using liquid hydrogen is planned and the engine components such as pre-cooler, core engine, afterburner and exhaust nozzle are under development. The engine components were tested under Mach 4 simulating condition by connecting the pre-cooler inlet to an air supply facility. The engine was tested in a propulsion wind tunnel with Mach 4 flight condition. Liquid nitrogen was supplied to the pre-cooler as a coolant in place of liquid hydrogen. Gaseous hydrogen was supplied to the main burner to drive the turbine with the combustion gas. As a result, high temperature structure and cooling system was proved to endure Mach 4 high temperature airstream. Wind-mill starting sequence of the core engine under Mach 4 flight condition was confirmed. Gross thrust of the core engine was obtained as an initial evaluation of elemental performance.

Silicon mounds fabricated on the Si(1 0 0)2×1 surface by a tip of a scanning tunneling microscope (STM) have been observed by STM at substrate temperature of 770 K. The shape of the mound is a quadrangular pyramid with facets of regular array of steps with double layer height. For all the step, the dimer rows are perpendicular to the step edges, so called the D B step. Just after the fabrication, the pyramid begins to decay immediately layer-by-layer. During decay, the D B steps move scarcely, but only the S B steps at the bottom layer move due to attachment and detachment of atoms which are detached from the upper layers. For a single layer mound, the aspect ratio of the mound oscillates between about 2.5 and 1.5.

Surface diffusion during decay of a two-dimensional (2D) island at approximately 800 K on Si(100) is studied using kinetic Monte Carlo simulation and scanning tunneling microscopy (STM). The decay is a diffusion-limited attachment/detachment process, but the diffusion is not that of a specific adatom from the island. The diffusing adatom is substituted by a terrace atom via a process in which the diffusing adatom fills a vacancy left behind by the hopping up of a terrace atom, which then becomes a diffusing adatom.

Various thiols are converted to disulfides by this operationally simple and environmentally friendly new method.