Introduction to special issue on "Long-term changes and trends in the stratosphere, mesosphere, thermosphere and ionosphere"

This special issue bundles some of the latest results on decadal-scale variations in the stratosphere, mesosphere, thermosphere, and ionosphere, following on from the 8th Workshop on Long-Term Changes and Trends in the Atmosphere, held in Cambridge, UK, on 28–31 July 2014. Emmert et al. (2015) provided a short report of the workshop. This introduction briefly describes the relevance of the field and highlights some of the recent progress that has been mad

Transfer Learning for Content-Based Recommender Systems using Tree Matching

In this paper we present a new approach to content-based transfer learning for solving the data sparsity problem in cases when the users' preferences in the target domain are either scarce or unavailable, but the necessary information on the preferences exists in another domain. We show that training a system to use such information across domains can produce better performance. Specifically, we represent users' behavior patterns based on topological graph structures. Each behavior pattern represents the behavior of a set of users, when the users' behavior is defined as the items they rated and the items' rating values. In the next step we find a correlation between behavior patterns in the source domain and behavior patterns in the target domain. This mapping is considered a bridge between the two domains. Based on the correlation and content-attributes of the items, we train a machine learning model to predict users' ratings in the target domain. When we compare our approach to the popularity approach and KNN-cross-domain on a real world dataset, the results show that on an average of 83$$ of the cases our approach outperforms both methods

Effects of Internal Configuration on Afterburner Shell Temperatures

A brief investigation was conducted in the altitude wind tunnel to determine the extent to which the afterburner shell cooling problem could be alleviated by internal configuration changes. Data were obtained with and without a cooling liner installed and for variations in the radial fuel distribution and in the radial distribution in flame-seat area. Consideration is given to the effects on both shell temperature and afterburner performance. In the range of fuel-air ratio investigated, the use of a cooling liner resulted in substantial reductions in shell temperature with no penalty in performance. Appreciable reductions in afterburner shell temperature were made possible by control of the radial fuel distribution; however, the effects on performance are uncertain and may depend on other variables not investigated. No direct relation was found between shell temperature and the clearance between the flame holder and the shell; however, some cooling effect may possibly be achieved by varying the clearance

Full-scale Investigation of Cooling Shroud and Ejector Nozzle for a Turbojet Engine : Afterburner Installation

A full-scale ejector cooling investigation was made on a turbojet engine - afterburner installation in the NACA Lewis altitude wind tunnel. Ejector performance was studied at primary exhaust-gas temperatures from 2700 degrees to 3400 degrees R (corresponding to ejector temperature ratios from 2.0 to 5.0), primary pressure ratios from 1.79 to 3.4, secondary air flows up to 29 percent of the primary gas flow, and for diameter ratios from 1.08 to 1.42 and spacing ratios from 0.04 to 1.16. In addition, variations were made in the primary exhaust-nozzle area. Ejectors with large diameter ratios permit the attainment of high gas flow ratios, but the jet-thrust losses become prohibitive as the spacing ratio is increased from 0 to 0.16. As the ejector diameter is reduced, the obtainable gas-flow ratio and the thrust loss are reduced. Previous results showing that data obtained at a temperature ratio of 1.0 could not be extrapolated to determine ejector performance at high temperature ratios by the application of the temperature ratio factor to the gas-flow ratios are substantiated by the present investigation

Altitude Performance Characteristics of Tail-pipe Burner with Variable-area Exhaust Nozzle

An investigation was conducted in the NACA Lewis altitude wind tunnel to determine effect of altitude and flight Mach number on performance of tail-pipe burner equipped with variable-area exhaust nozzle and installed on full-scale turbojet engine. At a given flight Mach number, with constant exhaust-gas and turbine-outlet temperatures, increasing altitude lowered the tail-pipe combustion efficiency and raised the specific fuel consumption while the augmented thrust ratio remained approximately constant. At a given altitude, increasing flight Mach number raised the combustion efficiency and augmented thrust ratio and lowered the specific fuel consumption