Attachment is defined as the formation of a relationship between a mother and her newborn infant. The concept of attachment has been inadequately defined and often confused with feelings associated with love, instinct, engrossment, and being connected to others. Prematurity and associated maternal-infant separation at birth can affect the attachment process. In this article, a research project, using Leninger's ethnonursing approach is described. Leninger's method was chosen to study the phenomenon of attachment in a neonatal intensive care unit (NICU). Ethnonursing has been found to be a suitable approach for the study of complex situations. Ethnonursing is based on an observation, participation in care, and reflection model. Qualitative data for this study were collected by observation, participation in care, and interviews of mothers (N = 25) in a tertiary NICU. Data were analyzed by comparison of narratives from field notes and transcripts. Findings from the analysis indicate the process of attachment was not automatic. Attachment should be considered as an individualized process. Two dichotomies associated with attachment were identified through the research. These were overt and covert attachment processes and may be dependent on the health status of the infant and the mother, environmental circumstances, and on the quality of care the infant receives.
Experimentalresults are presented for the aerodynamics and acoustics of an unswept wing with a half-span flap and a full-span slat. Concurrent aerodynamic and acoustic measurements were obtained for high-lift riggings representative of landing-approach configurations.Phased microphone array measurements indicate that slat gap noise is most significant for high slat deflections where the slat is lightly loaded. More specifically, the peak noise level for the 25deg slat deflection was 20 dB higher than that of the 9-deg slat deflection. Measurements of intermediate angles indicate a gradual decrease in slat noise as slat deflection is decreased. Strouhal frequency scaling of the 25deg slat configuration suggests that vortex shedding from the slat trailing edge may be an important noise mechanism. However, a non-linear relationship between slat noise level and angle of attack suggests a more complex phenomenon. Computational results detail the strength of the shear layers in the slatcove flow field. Variations in the slat-cove shear layers with slat deflection and angle of attack are presented. From correlations between the computed results and the measured acoustics, it is hypothesized that a KelvinHelmholtz instability develops in the slat cove and a feedback mechanism forms between the slat-cove and slat trailing-edge flow fields. Nomenb 6 wing span wing chord section lift coefficient = P / qc CL total lift coefficient = L / qS CP pressure coefficient = (p -pm) / q d distance from dividing streamline e section lift L total lift LP sound pressure level, dB re 20 pPa
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