Large expert-curated database for benchmarking document similarity detection in biomedical literature search

Document recommendation systems for locating relevant literature have mostly relied on methods developed a decade ago. This is largely due to the lack of a large offline gold-standard benchmark of relevant documents that cover a variety of research fields such that newly developed literature search techniques can be compared, improved and translated into practice. To overcome this bottleneck, we have established the RElevant LIterature SearcH consortium consisting of more than 1500 scientists from 84 countries, who have collectively annotated the relevance of over 180 000 PubMed-listed articles with regard to their respective seed (input) article/s. The majority of annotations were contributed by highly experienced, original authors of the seed articles. The collected data cover 76% of all unique PubMed Medical Subject Headings descriptors. No systematic biases were observed across different experience levels, research fields or time spent on annotations. More importantly, annotations of the same document pairs contributed by different scientists were highly concordant. We further show that the three representative baseline methods used to generate recommended articles for evaluation (Okapi Best Matching 25, Term Frequency–Inverse Document Frequency and PubMed Related Articles) had similar overall performances. Additionally, we found that these methods each tend to produce distinct collections of recommended articles, suggesting that a hybrid method may be required to completely capture all relevant articles. The established database server located at https://relishdb.ict.griffith.edu.au is freely available for the downloading of annotation data and the blind testing of new methods. We expect that this benchmark will be useful for stimulating the development of new powerful techniques for title and title/abstract-based search engines for relevant articles in biomedical research

Sristi - the NAL method for the design and analysis of natural laminar flow (NLP) airfoils

A software package (called SRISTI) for the design and analysis of NLF airfoils is described. As an illustration, an NLF airfoil for NAL's Light Transport Aircraft has been designed using this package. Its aerodynamic characteristics have been extensively compared with GAW-2 airfoil and also with wind tunnel experiments

The structure of strong shock waves using the Fokker-Planck model (Shock wave structure in monatomic gases, using Fokker-Planck model for particle collisions and Mott-Smith distribution for shock front)

The structure of strong shock waves in monatomic gases is studied using the Fokker-Planck model to represent the particle collisions and the Mott-Smith distribution to describe the distribution function within the shock front. The differential equation governing the variation of the density within the shock is derived by using the13; variational principle. The thickness of the shock front is evaluated numerically for various monatomic gases for Mach numbers varying from 2 to 20, and the variation of the shock thickness with viscosity is also studied for different gases. Several parameters of physical interest within the shock, such as density, temperature, and mean velocity of flow are evaluated numerically, and detailed curves showing their variation within the shock are presented for different Mach numbers. It is found that the temperature rises very steeply, reaches a maximum within a distance less than half the thickness of the shock, and then diminishes slowly to attain its asymptotic downstream values. The variation of the mean velocity is slow for weak shocks, but for higher Mach numbers, the mean velocity diminishes steeply and reaches the downstream values within half the thickness of the shock.13

Hypersonic flow around a blunt body - real gas effects

This paper deals with the real gas effects of the hypersonic flow over a cylinder with a blunt nose. The analysis is made using the Lighthill model of an ideal dissociating gas in equilibrium. The real gas effects on the high entropy layer adjacent to the body due to the curvature of the detached shock in front of the blunt nose have been evaluated for the cases Mx221E;=40 amp; Mx221E;=22 at different altitudes, using pure Oxygen as flowing media. The density profiles and the dissociation levels at various distances from the nose have been plotted. The proportion of Oxygen atoms remains considerable upto relative distances x/d =0(100) where d is the diameter of the nose base. It is found that a significant portion of the energy of the shock heated gas goes to dissociate the Oxygen molecules and the quantitative evaluation of this energy has been carried out

PCFLIGHT software and its application to the digital simulation of spin amp; recovery of an aircraft

'PCFLIGHT' is a PC based software pakage developed on PS 386/387 systems for digital flight simulation of an aircraft. As an example the spin simulation of mirage-3E and its recovery is carried out. The results agree quite well with those of the original report

SRISTI - Package for Design and analysis of Natural Laminar Flow Airfoils

SRISTI is a software package for design and analysis of a class of Natural Laminar Flow airfoils for general aviation application. It is developed on PS 386/387 and 13; PC 286/287 platforms.13; SRISIT is developed in C language; the interactive menu driven and user friendly environment is provided by a 13; C shell. The analysis part of the package uses an extensively tested code for evaluating the airfoil.13; It is also provided with a graphics interface to obtain aerodynamic performance curves

Determination of an optimum trajectory for a two stage rocket13; 13;

The optimum trajectory for a two-stage rocket for putting a pay load into a 100-nautical mile circular orbit is determined by an optm technique called SWIFT - Sequential Weight Increasing Faotor Technique. The optimum parameters-vertical rise time and pitch rate are compared with those obtained by empirical and other methods and found to be in excellent agreement. The present method is so general that it can be extended to 3D-Trajectory optimization

Approximation using rational splines with adjustable tension

An interpolation procedure using the rational spline approximation is presented . The rational spline contains an adjustable tension parameter for each pair of uccessive knots such that in the limit of zero tension, the spline reduces to a conventional cubic spline and in the limit of infinite tension the spline reduces to a straight line . The procedure for adjusting the tension parameters is completely automated such that by adjusting the tension it is possible to achieve the quot;bestquot; fit (in a least-squares sense) of the data .A detailed derivation of the algorithm is presented along with its procedural implementation.the method is successfully implemented on a computer and tested for two cases . Recommendations are made for further extension and application of this method

Evaluation of the transonic wave drag integral with particular reference to a real aircraft

The motivation for work on the wave drag integral was to carry out area ruling studies on an existing combat aircraft configuration. It is necessary (for discussion later on) to briefly recall the salient points. in the derivation of the wave drag integral