The Cycle of User-Responsive Collection Development in Digital Libraries

Traditional collection development strategies may not be sufficient to effectively expand the use of a digital library or repository. Librarians working on FRASER, a digital library of economic history that is both a subject and institutional repository, have developed a cyclical strategy of user-responsive collection development. Collections developed in response to stakeholder needs include materials on historic responses to mortgage defaults during the Great Depression, and on the causes of historic panics and depressions, which grew out of the research priorities of policymakers and economists during the financial crisis of 2007. This session will provide an overview of FRASER’s traditional collection development policy and demonstrate the cyclical model of user-responsive collecting with concrete use cases

Installed F/A-18 inlet flow calculations at 30 degrees angle-of-attack: A comparative study

NASA Lewis is currently engaged in a research effort as a team member of the High Alpha Technology Program (HATP) within NASA. This program utilizes a specially equipped F/A-18, the High Alpha Research Vehicle (HARV), in an ambitious effort to improve the maneuverability of high-performance military aircraft at low subsonic speed, high angle of attack conditions. The overall objective of the Lewis effort is to develop inlet technology that will ensure efficient airflow delivery to the engine during these maneuvers. One part of the Lewis approach utilizes computational fluid dynamics codes to predict the installed performance of inlets for these highly maneuverable aircraft. Full Navier-Stokes (FNS) calculations on the installed F/A-18 inlet at 30 degrees angle of attack, 0 degrees yaw, and a freestream Mach number of 0.2 have been obtained in this study using an algebraic turbulence model with two grids (original and revised). Results obtained with the original grid were used to determine where further grid refinements and additional geometry were needed. In order to account properly for the external effects, the forebody, leading edge extension (LEX), ramp, and wing were included with inlet geometry. In the original grid, the diverter, LEX slot, and leading edge flap were not included due to insufficient geometry definition, but were included in a revised grid. In addition, a thin-layer Navier-Stokes (TLNS) code is used with the revised grid and the numerical results are compared to those obtained with the FNS code. The TLNS code was used to evaluate the effects on the solution using a code with more recent CFD developments such as upwinding with TVD schemes versus central differencing with artificial dissipation. The calculations are compared to a limited amount of available experimental data. The predicted forebody/fuselage surface static pressures compared well with data of all solutions. The predicted trajectory of the vortex generated under the LEX was different for each solution. These discrepancies are attributed to differences in the grid resolution and turbulence modeling. All solutions predict that this vortex is ingested by the inlet. The predicted inlet total pressure recoveries are lower than data and the distortions are higher than data. The results obtained with the revised grid were significantly improved from the original grid results. The original grid results indicated the ingested vortex migrated to the engine face and caused additional distortions to those already present due to secondary flow development. The revised grid results indicate that the ingested vortex is dissipated along the inlet duct inboard wall. The TLNS results indicate the flow at the engine face was much more distorted than the FNS results and is attributed to the pole boundary condition introducing numerical distortions into the flow field

Thin-layer and full Navier-Stokes calculations for turbulent supersonic flow over a cone at an angle of attack

The proper use of a computational fluid dynamics code requires a good understanding of the particular code being applied. In this report the application of CFL3D, a thin-layer Navier-Stokes code, is compared with the results obtained from PARC3D, a full Navier-Stokes code. In order to gain an understanding of the use of this code, a simple problem was chosen in which several key features of the code could be exercised. The problem chosen is a cone in supersonic flow at an angle of attack. The issues of grid resolution, grid blocking, and multigridding with CFL3D are explored. The use of multigridding resulted in a significant reduction in the computational time required to solve the problem. Solutions obtained are compared with the results using the full Navier-Stokes equations solver PARC3D. The results obtained with the CFL3D code compared well with the PARC3D solutions

Frutales tropicales de la región caribe insectos plaga y agentes entomológicos benéficos

Se describen algunos insectos dañinos de los frutales tropicales y los principales agentes para el control biológico. Se indica el comportamiento de los insectos plagas, sus hábitos alimenticios, su papel como vectores de enfermedades y los daños que causan. Entre los insectos chupadores se mencionán el ácaro tostador Phyllocoptruta oleivora en cítricos, la arañita roja Brevipalpus sp., en mango y papaya y el trips de la fruta, Selenotrhips rubrocinctus en mango. Se indican los insectos que deterioran las frutas en la región como son las moscas Anastrepha y Ceralitis respectivamente. Se señalan algunos agentes de control biológico para sitios y depredadores de los géneros Apanteles, Trichogramma, Chrysopa Caleonegilla y Cycloneda, así como hongos entomopatógenos como Bacillus thurigiensis, Nomurea rileyii y Beauveria bassiana. Se ofrecen algunos criterios para el monitoreo entomológico en algunos frutales tropicale

Evaluation of F/A-18A HARV inlet flow analysis with flight data

The F/A-18A aircraft has experienced engine stalls at high angles-of-attack and yaw flight conditions which were outside of its flight envelope. Future aircraft may be designed to operate routinely in this flight regime. Therefore, it is essential that an understanding of the inlet flow field at these flight conditions be obtained. Due to the complex interactions of the fuselage and inlet flow fields, a study of the flow within the inlet must also include external effects. Full Navier-Stokes (FNS) calculations on the F/A-18A High Alpha Research Vehicle (HARV) inlet for several angles-of-attack with sideslip and free stream Mach numbers have been obtained. The predicted forebody/fuselage surface static pressures agreed well with flight data. The surface static pressures along the inlet lip are in good agreement with the numerical predictions. The major departure in agreement is along the bottom of the lip at 30 deg and 60 deg angle-of-attack where a possible streamwise flow separation is not being predicted by the code. The circumferential pressure distributions at the engine face are in very good agreement with the numerical results. The variation in surface static pressure in the circumferential direction is very small with the exception of 60 angle-of-attack. Although the simulation does not include the effect of the engine, it appears that this omission has a second order effect on the circumferential pressure distribution. An examination of the unsteady flight test data base has shown that the secondary vortex migrates a significant distance with time. In fact, the extent of this migration increases with angle-of-attack with increasing levels of distortion. The effects of the engine on this vortex movement is unknown. This implies that the level of flow unsteadiness increases with increasing distortion. Since the computational results represent an asymptotic solution driven by steady boundary conditions, these numerical results may represent an arbitrary point in time. A comparison of the predicted total pressure contours with flight data indicates that the numerical results are within the excursion range of the unsteady data which is the best the calculations can attain unless an unsteady simulation is performed

Control of acetylcholine receptor mobility and distribution in cultured muscle membranes. A fluorescence study

The molecular control of the distribution and motion of acetylcholine receptors in the plasma membrane of developing rat myotubes in primary cell culture was investigated by fluorescence techniques. Acetylcholine receptors were marked with tetramethylrhodamine-labeled [alpha]-bungarotoxin and lateral molecular motion in the membrane was measured by the fluorescence photobleaching recovery technique. Three types of experiments are discussed: (I) The effect of enzymatic cleavages, drugs, cross-linkers, and physiological alterations on the lateral motion of acetylcholine receptors and on the characteristic distribution of acetylcholine receptors into patch and diffuse areas. (II) Observation of the distribution and/or motion of fluorescence-labeled concanavalin A receptors, lipid probes, cell surface protein, and stained cholinesterase in acetylcholine receptor patch and diffuse areas. (III) The effect of a protein synthesis inhibitor and electrical stimulation on membrane incorporation of new acetylcholine receptors.Some of the main conclusions are: (a) acetylcholine receptor lateral motion is inhibited by concanavalin A plant lectin and by anti-[alpha]-bungarotoxin antibody, but marginally enhanced by treatment with a local anesthetic; (b) patches are stabilized by an immobile cellular structure consisting of molecules other than the acetylcholine receptors themselves; (c) this structure is highly selective for acetylcholine receptors and not for other cell membrane components; (d) acetylcholine receptor patch integrity and diffuse area motion are independent of direct metabolic energy requirements and are sensitive to electrical excitation of myotube; (e) lipid molecules can move laterally in both acetylcholine receptor patches and diffuse areas; and (f) acetylcholine receptor lateral motion in diffuse areas and immobility in patch areas are not altered by specific agents which are known to affect extrinsic cell surface proteins, or cytoplasmic microfilaments and microtubules.Peer Reviewedhttp://deepblue.lib.umich.edu/bitstream/2027.42/22569/1/0000114.pd

Modulo del cultivo de la guayaba

El guayabo Psidium guajaba L., es una planta de la familia de las mirtáceas, originario de América Tropical, en donde se encuentra tanto en forma silvestre como cultivada desde México hasta Brasil. El género Psidium, al cual pertenece en guayaba consta de unas 150 especies de las cuales una docena han sido estudiadas y seleccionadas para mejorar la calidad y aumentar la productividad.Guayaba-Psidium guajav