Relationship between tonic and phasic craving for alcohol.

BackgroundMultiple measures are utilized to assess alcohol craving, often interchangeably. Little is known about the relationship between tonic and phasic craving. This study fills this gap in the literature by examining the association between tonic levels of alcohol craving and phasic craving for alcohol that is provoked by alcohol administration.MethodsForty-three non-treatment seeking problem drinkers underwent an initial interview and two laboratory testing sessions, where either alcohol or a saline placebo was administered intravenously. Tonic craving was assessed via the Penn Alcohol Craving Scale (PACS) and Obsessive Compulsive Drinking Scale (OCDS) at the initial interview. Phasic craving was assessed during the laboratory sessions (i.e., alcohol and saline administrations, single blinded) at baseline and at 3 subsequent breath alcohol concentrations (0.02, 0.04, and 0.06 g/dl).ResultsThere was a main effect of PACS in predicting phasic craving across both saline and alcohol administration conditions (p < 0.05). The OCDS was predictive of phasic craving when alcohol, but not saline, was administered (p = 0.058); the obsessive subscale (p = 0.01), but not the compulsive subscale (p > 0.10), predicted phasic craving during alcohol, as compared to saline administration.ConclusionIn sum, tonic craving captured by the OCDS was predictive of phasic craving during alcohol administration whereas the PACS more generally captured the increase in phasic craving. Therefore, these measures of tonic craving may function differently in capturing the experience of phasic craving. Implications for the utilization of the PACS and OCDS as well as assessments of craving in alcoholism research are discussed

Nuclear energy density functionals: what we can learn about/from their global performance?

A short review of recent results on the global performance of covariant energy density functionals is presented. It is focused on the analysis of the accuracy of the description of physical observables of ground and excited states as well as to related theoretical uncertainties. In addition, a global analysis of pairing properties is presented and the impact of pairing on the position of two-neutron drip line is discussed.Comment: 11 pages, 9 figures, Proceedings of the conference on Nuclei and Mesoscopic Physics 2014, MS

Convergence between the Penn Alcohol Craving Scale and diagnostic interview for the assessment of alcohol craving.

IntroductionThe Penn Alcohol Craving Scale (PACS) is one of the most widely used instruments to measure craving for alcohol. Recent research has suggested that scores on the PACS can be used as a "stand in" for the diagnostic criterion of alcohol craving with a proposed cutoff of >20 on the PACS indicating a "positive" alcohol craving symptom. The present study examined the convergence between the PACS and face-to-face diagnostic interview for the assessment of alcohol craving.MethodA sample of non-treatment seeking heavy drinkers (N = 338) enrolled in experimental studies of AUD completed the PACS as well as a face-to-face diagnostic interview for AUD, which included the craving item from the Semi-Structured Assessment for the Genetics of Alcoholism (SSAGA).ResultsUsing the PACS cut-off score of >20, 12.9% (N = 43) of the sample met criteria for alcohol craving compared to 21% (N = 74) of the sample meeting criteria based on the diagnostic interview. Using the PACS cutoff of >20, sensitivity (i.e., true positive rate) was 41% and specificity (i.e., true negative rate) was 95%. Exploratory analyses suggested that a cut-off score of ≥15 achieved the optimal balance of sensitivity (67%) and specificity (81%) in our sample.ConclusionsAdvancing the assessment of alcohol craving and the conversion from DSM-IV to DSM-5 diagnostic criteria represents an important research direction. The present study recommends that a PACS score cut off of ≥15 should be used as an indicator of clinically significant alcohol craving in community samples of non-treatment seekers

High Reynolds number tests of the CAST 10-2/DOA 2 airfoil in the Langley 0.3-meter transonic cryogenic tunnel, phase 1

A wind tunnel investigation of an advanced technology airfoil, the CAST 10-2/DOA 2, was conducted in the Langley 0.3 meter Transonic Cryogenic Tunnel (0.3 m TCT). This was the first of a series of tests conducted in a cooperative National Aeronautics and Space Administration (NASA) and the Deutsche Forschungs- und Versuchsanstalt fur Luft- und Raumfahrt e. V. (DFVLR) airfoil research program. Test temperature was varied from 280 K to 100 K to pressures from slightly above 1 to 5.8 atmospheres. Mach number was varied from 0.60 to 0.80, and the Reynolds number (based on airfoil chord) was varied from 4 x 10 to the 8th power to 45 x 10 to the 6th power. This report presents the experimental aerodynamic data obtained for the airfoil and includes descriptions of the airfoil model, the 0.3 m TCT, the test instrumentation, and the testing procedures

Analysis of validation tests of the Langley pilot transonic cryogenic tunnel

A pilot transonic cryogenic pressure tunnel has recently been developed and proof tested at the NASA Langley Research Center. In addition to providing an attractive method for obtaining high Reynolds number results at moderate aerodynamic loadings and tunnel power, this unique tunnel allows the independent determination of the effects of Reynolds number, Mach number, and dynamic pressure (aeroelasticity) on the aerodynamic characteristics of the model under test. The proof of concept experimental and theoretical studies are briefly reviewed. Experimental results obtained on both two- and three-dimensional models have substantiated that cryogenic test conditions can be set accurately and that cryogenic gaseous nitrogen is a valid test medium

Simulation of flight test conditions in the Langley pilot transonic cryogenic tunnel

The theory and advantages of the cryogenic tunnel concept are briefly reviewed. The unique ability to vary temperature independently of pressure and Mach number allows, in addition to large reductions in model loads and tunnel power, the independent determination of Reynolds number, Mach number, and aeroelastic effects on the aerodynamic characteristics of the model. Various combinations of Reynolds number and dynamic pressure are established to represent accurately flight variations of aeroelastic deformation with altitude changes. The consequences of the thermal and caloric imperfections of the test gas under cryogenic conditions were examined and found to be insignificant for operating pressures up to 5 atm. The characteristics of the Langley pilot transonic cryogenic tunnel are described and the results of initial tunnel operation are presented. Tests of a two-dimensional airfoil at a Mach number of 0.85 show identical pressure distributions for a chord Reynolds number of 8,600,000 obtained first at a stagnation pressure of 4.91 atm at a stagnation temperature of 322.0 K and then at a stagnation pressure of 1.19 atm at a stagnation temperature of 116.5 K