bluuebunny/crossref_metadata_2025_split huggingface dataset:
A Concise Set of Structure and Process Indicators to Assess and Compare Antimicrobial Stewardship Programs Among EU and US Hospitals: Results From a Multinational Expert Panel
Authors: Pollack Lori A. , Plachouras Diamantis , Sinkowitz-Cochran Ronda , Gruhler Heidi , Monnet Dominique L. , Weber J. Todd ,   Transatlantic Taskforce on Antimicrobial Resistance (TATFAR) Expert Panel on Stewardship Structure and Process Indicators
Published: July 2016

OBJECTIVESTo develop common indicators, relevant to both EU member states and the United States, that characterize and allow for meaningful comparison of antimicrobial stewardship programs among different countries and healthcare systems.DESIGNModified Delphi process.PARTICIPANTSA multinational panel of 20 experts in antimicrobial stewardship.METHODSPotential indicators were rated on the perceived feasibility to implement and measure each indicator and clinical importance for optimizing appropriate antimicrobial prescribing.RESULTSThe outcome was a set of 33 indicators developed to characterize the infrastructure and activities of hospital antimicrobial stewardship programs. Among them 17 indicators were considered essential to characterize an antimicrobial stewardship program and therefore were included in a core set of indicators. The remaining 16 indicators were considered optional indicators and included in a supplemental set.CONCLUSIONSThe integration of these indicators in public health surveillance and special studies will lead to a better understanding of best practices in antimicrobial stewardship. Additionally, future studies can explore the association of hospital antimicrobial stewardship programs to antimicrobial use and resistance.Infect Control Hosp Epidemiol 2016:1–11
THE TEACHING AND PRACTICE OF FILIAL PIETY IN BUDDHISM
Authors: Xing Guang 
Published: July 2016

AbstractBuddhist scholars like Kenneth Ch'en have argued that the teaching of filial piety was a special feature of Chinese Buddhism as a response to the Chinese culture. Others, among them John Strong and Gregory Schopen, have shown that filial piety was also important in Indian Buddhism, but Strong does not consider it integral to the belief system and Schopen did not find evidence of it in early writings he examined. In this article, through an analysis of early Buddhist resources, the Nikāyas and Āgamas, I demonstrate that the practice of filial piety has been the chief good karma in the Buddhist moral teaching since its inception, although it is not as foundational for Buddhist ethics as it is for Confucian ethics. The Buddha advised people to honor parents as the Brahmā, the supreme god and the creator of human beings in Hinduism, as parents have done much for their children. Hence, Buddhism teaches its followers to pay their debts to parents by supporting and respecting them, actions that are considered the first of all meritorious deeds, or good karma, in Buddhist moral teachings. Moreover, according to the Buddhist teaching of karma, matricide and patricide are considered two of the five gravest bad deeds, and the consequence is immediate rebirth in hell. Mahāyāna Buddhism developed the idea of filial piety further and formulated the four debts to four groups of people—parents, sentient beings, rulers, and Buddhism—a teaching that became very popular in Chinese Buddhism and spread to other East Asian countries.
The Calculation of Potential Derivatives by Using NBIE for Anisotropic Potential Problems
Authors: Zhou H.-L. , Bian B.-X. , Tian Y. , Yu B. , Niu Z.-R. 
Published: July 2016

AbstractThe natural boundary integral equation (NBIE) is developed to calculate potential derivatives for potential problems with anisotropic media. Firstly, the governing equation of the two-dimensional anisotropic potential problem is transformed into standard Laplace equation by a coordinate transformation method. Then a potential derivative boundary integral equation named as NBIE is extended to solve the anisotropic potential problem. The most important virtue of the NBIE is that the singularity of the integral kernel function is reduced by one order in comparison with the conventional potential derivative boundary integral equation(CDBIE). Therefore the new potential derivative boundary integral equation only contains strongly singular integrals rather than hyper-singular integrals. Thus the NBIE can calculate more accurate potential derivative results for both boundary nodes and interior points. Moreover, in combination with the analytical integral regularization algorithm of nearly singular integrals, the NBIE can obtain more accurate potential derivatives of interior points very close to the boundary than the CDBIE. Numerical examples on heat conduction in anisotropic media demonstrate the accuracy and efficiency of the NBIE.
A note on subsonic aerofoil theory
Authors: Miles John W. 
Published: July 2016

SummaryA linearised theory for the subsonic, lifting surface problem is formulated in terms of Fourier integral solutions to Laplace’s equation. The symmetric and anti-symmetric problems of the first kind are solved explicitly, while the problems of the second kind depend on the solution of dual integral equations. The antisymmetric problem of the second kind is cast in a variational form, from which certain well-known theorems may be deduced.
Supersonic Flow Past Bodies of Revolution with Thin Wings of Small Aspect Ratio
Authors: Stocker P. M. 
Published: July 2016

SummaryThe method developed by G. N. Ward for the treatment of slender pointed bodies in a uniform supersonic stream is applied to three special cases.
(i)Supersonic flow past a body of revolution with thin wings of symmetrical section and of small aspect ratio at zero incidence.(ii)Supersonic flow past a body of revolution with plane wings of small aspect ratio set at incidence to the body, the whole being at incidence to the stream.(iii)Supersonic flow past a body of revolution with a plane fin of small aspect ratio set at incidence, the whole being at incidence to the stream.The pressure distribution on the wing has been calculated for a special case of (i) and is given in the Appendix.
A New Approach to Thin Aerofoil Theory
Authors: Lighthill M.J. 
Published: July 2016

SummaryThe general technique for rendering approximate solutions to physical problems uniformly valid is here applied to the simplest form of the problem of correcting the theory of thin wings near a rounded leading edge. The flow investigated is two-dimensional, irrotational and incompressible, and therefore the results do not materially add to our already extensive knowledge of this subject, but the method, which is here satisfactorily checked against this knowledge, shows promise of extension to three-dimensional, and compressible, flow problems.The conclusion, in the problem studied here, is that the velocity field obtained by a straightforward expansion in powers of the disturbances, up to and including either the first or the second power, with coefficients functions of co-ordinates such that the leading edge is at the origin and the aerofoil chord is one of the axes, may be rendered a valid first approximation near the leading edge, as well as a valid first or second approximation away from it, if the whole field is shifted downstream parallel to the chord for a distance of half the leading edge radius of curvature ρL. It follows that the fluid speed on the aerofoil surface, as given on such a straightforward second approximation as a function of distance x along the chord, similarly is rendered uniformly valid (see equation (52)) if the part singular like x-1 is subtracted and the remainder is multiplied by .
Supersonic Flow over Thin Symmetrical Wings with Given Surface Pressure Distribution
Authors: Goldsworthy F. A. 
Published: July 2016

SummaryThe inverse problem of determining the supersonic flow past a thin symmetrical wing at zero incidence with given surface pressure distribution is solved for wings of arbitrary plan form. Expressions are obtained for the vertical derivative of the potential on the wing surface from which, using the linearised boundary condition of zero normal velocity at the surface, the profile of the wing can be designed. The integral equation method adopted by J. C. Evvard and extended by G. N. Ward is used. The analysis cannot be applied to pointed wings, whose leading edges are subsonic. The results in Part I are completely general and are applied to specific problems in Part II.
A note on the performance of ducted fans
Authors: Thwaites Bryan 
Published: July 2016

SummaryThe strip-theory equations of flow through a ducted fan were the basis of a method of designing a fan for a given performance. The merit of the method was that it amounted to an explicit solution of the design problem, no iteration being necessary.In the inverse problem, of determining the flow past a given fan in conditions other than those of the design, two relations—the motor or tunnel characteristics, for example—will be given between the four quantities P, Ω, η, u (the motor power and angular velocity, the fan efficiency and the air speed at the fan). The problem is to determine the values of these four quantities together with details of the flow past any blade element.This paper shows that to a high degree of accuracy the performance of a ducted fan can be summed up by saying that P/Ω3 and η are both functions of Ω/u only, functions which depend only on the fan shape. Solution by graphical means is therefore almost instantaneous.The fan-tunnel combination is shown to be governed by extremely simple equations which amount to saying that the tunnel power factor is a function of Ω/u only which, again, can be calculated once for all for a given fan and tunnel.
Photoelastic Investigation on Plates with Single Interference-Fit Pins with Load Applied (a) to Pin only and (b) to Pin and Plate Simultaneously
Authors: Jessop H. T. , Snell C. , Holister G. S. 
Published: July 2016

SummaryThe reduction in stress concentration factors resulting from the introduction of an interference-fit pin in a circular hole in a flat plate to which a simple tension is applied has already been recorded. The same result is found to occur to an equally marked extent, and qualitatively in a very similar way, when the load is applied to the pin itself. When varying loads are applied to the pin or the plate, the effect of the interference is to produce a rise in the mean stress level at critical points on the hole boundary with a marked fall in the oscillatory stress. There appears to be an optimum value for the “interference stress” for given applied loading conditions at which the endurance of the plate will have its highest value.When loads are applied simultaneously to pin and plate the critical stress on the hole boundary is found to be the mean of the stresses which would be produced by the total load applied separately to the pin and to the plate.
Graphite: A Future Structural Material
Authors: Kennedy A. J. 
Published: July 2016

SummaryGraphite is a material with unique high-temperature properties. Its strength and modulus increase with temperature up to about 2000-2500°C., in which range it exhibits a higher strength than any known material. The development of new types of graphite (such as pyrolytic graphite, deposited from the vapour) and impregnated graphites, are both significant to future technology. The highly-oriented pyrolytic graphites in particular, with their marked thermal and mechanical anisotropy, and their superior mechanical properties (60 x 103lb./in.2strength at 2750°C, with 60 per cent ductility) offer distinct possibilities, particularly in composite structures. Graphite sublimes directly from the solid to vapour phase at 3700°C. at atmospheric pressure. As the sublimation energy is high, it is, at least in theory, a very efficient ablating material. It also has a high creep resistance. Surface reactions limit its value, particularly in oxidising environments, and coatings, or other methods of surface protection, are of high importance. The modulus of graphite is low, being about one-half of that for lead at room temperature, increasing with temperature to a maximum in the region of 2200°C. The properties vary in detail from one type of graphite to another, and with the direction in which measurements are made. Graphite has a low density (about 2·0) and is comparatively cheap, so that its low temperature limitations (zero ductility at room temperature) may be offset, at least in part, by a re-appraisal of the design factors. It can be joined and fabricated fairly readily, and appears to be a material of great value to advanced high-temperature projects in the future, where composite assemblies of various kinds will be essential.
The Vibration of Air in a Duct with a Subsonic Mean Flow
Authors: Whitehead D. S. 
Published: July 2016

SummaryThe effect of a subsonic mean flow on the organ-pipe type of vibration of the air in a duct of uniform area is calculated. The flow at entry to the duct is assumed to be at constant stagnation pressure, and a range of exit conditions is considered. It is found that the effect of the mean flow is to reduce the resonant frequencies by a factor of (1—M2) (where M is the Mach number in the duct) and to introduce damping of the vibration. Except when the duct is terminated by an efficient diffuser, this damping is rather large and it would require a powerful driving mechanism to produce large vibrations in the duct.
On the Interpretation of the Vector Plots of Forced Vibrations of a Linear System with Viscous Damping
Authors: Woodcock D. L. 
Published: July 2016

SummaryA new method of analysing the response of linear systems to sinusoidal excitation, which avoids the assumptions of present methods, is developed in this paper. It enables one to obtain the eigenvalues and righthand eigenvectors of a system with viscous damping from the response of the system. If the inertia matrix of the system is known, the damping and stiffness matrices can also be obtained. No assumptions are made about the form of these matrices, and the method is not restricted to systems with only small amounts of damping.
The Effect of Lumped Parameters on Beam Frequencies
Authors: Leckie F. A. , Lindberg G.M. 
Published: July 2016

SummaryAn investigation has been made into the errors involved in using certain lumped parameter methods for the solution of beam frequencies. It is found that existing methods are not consistent for all boundary conditions. A new dynamic stiffness matrix has been formulated, which gives consistently good results for even a few elements. The error in the solution is always inversely proportional to the fourth power of the number of elements used.
Aerodynamic and Thermodynamic Effects of Coolant Injection on Axial Compressors
Authors: Hill P. G. 
Published: July 2016

SummaryA study has been made of the effects of inlet coolant injection upon axial compressor performance, using the results of tests on turboshaft engines. It is shown that evaporation of the coolant changes the stage work distribution as well as the ideal compression work and that these effects may be estimated by elementary thermodynamic methods. Simplified prediction procedures are suggested and compared with experimental results.
Note on the Speed of Stall Propagation in a Cascade of Aerofoils
Authors: Cheers F. , Funnell G. C. 
Published: July 2016

SummaryFrom an investigation of published experimental results, it appears that three types of propagating stall cells occur on isolated blade rows. On stationary blade rows, and rotating rows which have the highest blade incidence at the tip, the speed of propagation seems to depend on a parameter based on the blade section near the leading edge, and in some experiments marked changes in this speed have been observed to coincide with changes in the form of stall on the individual blades. For rotating rows with the highest incidence at root or mid-section the speed of stall propagation lies within a fairly limited range and shows no dependence on the blade geometry. When the incidence is increased well beyond that at which stall first occurs, the stall cell pattern on most rotating rows changes from multiple cells to one or two of very large amplitude, with a marked change in speed of propagation.
The Turbulent Supersonic Base Pressure Problem: A Comparison between a Theory and Some Experimental Evidence
Authors: McDonald H. 
Published: July 2016

SummaryA comparative study is made of a recent theoretical approach to the problem of predicting the supersonic, turbulent base pressure and of the experimental evidence. The theory is based on the Chapman-Korst flow model of separated flows with a modified recompression process. Due allowance can be made for the presence of the initial boundary layer, with the limitation that its thickness must be less than about one step height at low Mach numbers, dropping to about one third of a step height at M=3·0. Fairly good agreement between the predicted and measured base pressure can be obtained although a predicted Reynolds number effect is not observed. The absence of this Reynolds number effect is. discussed in the light of recent experiments on flow mixing.
The Dynamic Response of Structural Members. An Improvement in Classical Methodology
Authors: Pilkey W. D. 
Published: July 2016

SummaryIt is shown that considerable improvement is achieved in the most popular classical approach to the vibration of structural members by giving new meaning to the generalised coordinate term in the infinite series expansion of the product of the generalised coordinate and eigenfunction. A transform employing the eigenfunction as a kernel efficiently generates a universal solution that embraces arbitrary loading, time-dependent boundary conditions, and such in-span conditions as supports and changes in cross section, axial load, and elastic foundation modulus. The method is applied to the Timoshenko beam as a representative structural member.
Calculated Pressure Distributions and Shock Shapes on Thick Conical Wings at High Supersonic Speeds
Authors: Squire L. C. 
Published: July 2016

SummaryIn recent papers Messiter and Hida have proposed a first-order correction to simple Newtonian theory for the pressure distributions on the lower surfaces of lifting conical bodies with detached shocks. The method involves the solution of an integral equation which Messiter solved numerically for thin delta wings, while Hida gave an approximate solution for thick wings with diamond and bi-convex cross-sections. It is shown in the present paper that Hida’s approximate solutions give poor agreement with experiment, and a series of more precise numerical solutions of the equation are given for wings with diamond cross-sections. The pressures, and shock shapes, obtained from these solutions are in very good agreement with experiment at Mach numbers as low as 4·0.The method has also been extended to Nonweiler wings at off-design when the shock wave is detached from the leading edges. Again the agreement with experiment is good provided the integral equation is solved numerically.
Application of the Discrete Element Method to the Buckling Analysis of Rectangular Plates under Arbitrary Membrane Loading
Authors: Dawe D. J. 
Published: July 2016

SummaryThe discrete element displacement method is used to analyse the instability of flat rectangular plates subjected to arbitrary systems of in-plane loading. Critical load intensities calculated in a range of applications, some of which include discrete reinforcing members, are compared with the predictions of past investigators and demonstrate the accuracy of the procedure.
Attitude Dynamics and Stability Conditions of a Non-Rigid Spinning Satellite
Authors: Rossi L. C. , Di San Martino R. C. Michelini , Ghigliazza R. 
Published: July 2016

SummaryThe attitude dynamics of a spinning satellite containing an elastically-restrained, viscously-damped mass, is investigated. This non-rigidity approximately represents the interesting practical case of equipment supported by relatively soft anti-shock mountings and the case of a particular viscous nutation damper. The linearised differential equations and the transfer functions relating the dynamic behaviour of the oscillating mass to the spinning-body components of the angular speed and the external torque are determined. On these grounds, the possibility of unstable configurations is singled out and discussed, and the stability condition is established, within the small perturbation approximations. Furthermore, the attitude dynamics for the satellite, both for large manoeuvres and fine corrections, is obtained by applying a train of pulsed torques by means of a suitable control logic and mass-ejection jets. The results are compared with those obtained from rigid-body theory. It is demonstrated that comparatively wide nutations may be produced, and the influence of the relevant parameters is determined.
An Unsteady Flow Wind Tunnel
Authors: Horlock J H 
Published: July 2016

SummaryA novel low-speed wind tunnel which produces unsteady “gust” flows is described. The walls are sinusoidal in shape and are moved in the flow direction with a velocity Wwless than the mean velocity Wmof the free stream. The tunnel is useful for testing isolated aerofoils and aerofoils in cascade in non-convective gusts (Ww< Wm) so that comparisons with predictions by thin aerofoil theory may be made. However, it does not simulate precisely the unsteady flow that occurs in axial flow turbomachines.
Generation of Weak Shock Waves in a Shock Tube
Authors: Dain C G , Hodgson J P 
Published: July 2016

SummaryThe properties of weak shock waves in a vibrationally relaxing gas are discussed with particular application to waves in carbon dioxide. An account of various methods of generating weak shock waves in a shock tube is given. The best method requires the insertion of a perforated plate in the low pressure section of the shock tube. A suitable choice for the open-to-total area ratio of the plate leads to transmitted waves in the appropriate strength regime. These waves were observed using a Mach-Zehnder interferometer and were either fully or partly dispersed by vibrational relaxation. Values for the relaxation frequency of carbon dioxide at room temperature were obtained.
Viscous Modelling of Wing-Generated Trailing Vortices
Authors: Williams Geoffrey M 
Published: July 2016

SummaryThe trailing vortex wake system generated by a lifting wing of finite span is modelled with a pair of laminar, viscous vortex models of a new type. The embryonic form of this viscous wake model is matched, at several interior collocation points, to the inviscid Betz model of the wake convolution process that transforms the wing trailing-edge vortex sheet into a pair of axisymmetric trailing vortices. In the near-wake and intermediate-wake regions downstream of the wing, the viscous wake model indicates that the trailing vortex characteristics (particularly the peak swirl velocity and the circulation profile) are strongly influenced by details of the wing span load distribution. Using simple eddy viscosity concepts, the viscous wake model achieves good qualitative agreement with test results from a limited selection of published experimental wake investigations. The present laminar theory appears to offer a useful basis for developing an engineering prediction method of aeroplane wake characteristics.