The boundary layer on compressor cascade blades

The purpose of NASA Research Grant NSG-3264 is to characterize the flowfield about an airfoil in a cascade at chord Reynolds number(R sub C)near 5 x 10 to the 5th power. The program is experimental and combines laser Doppler velocimeter (LDV) measurements with flow visualization techniques in order to obtain detailed flow data, e.g., boundary layer profiles, points of separation and the transition zone, on a cascade of highly-loaded compressor blades. The information provided by this study is to serve as benchmark data for the evaluation of current and future compressor cascade predictive models, in this way aiding in the compressor design process. Summarized is the research activity for the period 1 December 1985 through 1 June 1986. Progress made from 1 June 1979 through 1 December 1985 is presented. Detailed measurements have been completed at the initial cascade angle of 53 deg. (incidence angle 5 degrees). A three part study, based on that data, has been accepted as part of the 1986 Gas Turbine Conference and will be submitted for subsequent journal publication. Also presented are data for a second cascade angle of 45 deg (an incidence angle of 3 degrees)

The measurement of boundary layers on a compressor blade in cascade at high positive incidence angle. 2: Data report

Boundary layer and near-wake velocity measurements have been made in the well documented flow field about a double circular arc compressor blade in cascade, at an incidence angle of 5 deg. and a chord Reynolds number of 500,000. In Part 2 of this report these measurements were analyzed and presented in standard graphical format. The flow geometry, measurement techniques, and physics of the flow field were also discussed. In this, part 2 of the report, raw and analyzed data are presented in tabulated form in an attempt to make this data more accessible to computational comparison. Also included in part 2 is a description of the data analysis employed. A computer tape containing the data is available

The measurement of boundary layers on a compressor blade in cascade. Volume 1: Experimental technique, analysis and results

Measurements were made of the boundary layers and wakes about a highly loaded, double-circular-arc compressor blade in cascade. These laser Doppler velocimetry measurements have yielded a very detailed and precise data base with which to test the application of viscous computational codes to turbomachinery. In order to test the computational codes at off-design conditions, the data were acquired at a chord Reynolds number of 500,000 and at three incidence angles. Moreover, these measurements have supplied some physical insight into these very complex flows. Although some natural transition is evident, laminar boundary layers usually detach and subsequently reattach as either fully or intermittently turbulent boundary layers. These transitional separation bubbles play an important role in the development of most of the boundary layers and wakes measured in this cascade and the modeling or computing of these bubbles should prove to be the key aspect in computing the entire cascade flow field. In addition, the nonequilibrium turbulent boundary layers on these highly loaded blades always have some region of separation near the trailing edge of the suction surface. These separated flows, as well as the subsequent near wakes, show no similarity and should prove to be a challenging test for the viscous computational codes

Traditional architecture of Golęczewo and its impact on contemporary buildings

The work presents the results of research investigating traditional architecture in Golęczewo – a village near Poznań – and its impact on contemporary buildings. The analysis, which is one of the stages in the research on vernacular architecture of Wielkopolska, was performed using the author’s innovative method, which allows to determine the value of a building on the basis of the parameters of its architectural form and location. Its main goal was to identify traditional elements of buildings in Golęczewo and to confront tchem with modern forms of residential buildings erected after World War II. The research also aimed to define the relations between traditional and contemporary architecture, as well as search for best examples of modern architecture which invoke local building traditions. The author tries to answer the question whether today, when catalogues with standard house designs are widely available and guidelines are often not sufficient, contemporary buildings still seek to resemble the traditional architecture of region.Praca prezentuje wyniki badania dotyczącego tradycyjnej architektury w miejscowości Golęczewo koło Poznania oraz jej wpływu na zabudowę współczesną. Analiza, która stanowi jeden z etapów badań nad architekturą wernakularną Wielkopolski została przeprowadzona w oparciu o autorską metodę badawczą, pozwalającą na waloryzację budynków na podstawie parametrów ich formy architektonicznej oraz usytuowania. Jej głównym celem było zdefiniowanie tradycyjnych elementów architektury w danej miejscowości oraz skonfrontowanie ich z nowoczesnymi formami spotykanymi w budynkach mieszkalnych powstałych po II wojnie światowej. Przedmiotem badań było także określenie relacji między architekturą tradycyjną i współczesną oraz poszukiwanie najlepszych przykładów nowoczesnych budynków, które odwołują się do lokalnych tradycji budowlanych. Autor pracy poszukuje odpowiedzi na pytanie, czy w dobie ogólnie dostępnych katalogów domów typowych oraz nie zawsze wystarczających wytycznych zawartych w aktach prawa miejscowego, budynki współczesne odwołują się swoimi formami do tradycyjnej architektury regionu

The measurement of boundary layers on a compressor blade in cascade. Volume 2: Data tables

Measurements were made of the boundary layers and wakes about a highly loaded, double-circular-arc compressor blade in cascade. These laser Doppler velocimetry measurements have yielded a very detailed and precise data base with which to test the application of viscous computational codes to turbomachinery. In order to test the computational codes at off-design conditions, the data have been acquired at a chord Reynolds number of 500,000 and at three incidence angles. Average values and 95 percent confidence bands were tabularized for the velocity, local turbulence intensity, skewness, kurtosis, and percent backflow. Tables also exist for the blade static-pressure distributions and boundary layer velocity profiles reconstructed to account for the normal pressure gradient

The measurement of boundary layers on a compressor blade in cascade at high positive incidence angle. 1: Experimental techniques and results

Measurements of the mean velocity and turbulence intensity were made using a one-component laser Doppler velocimeter in the boundary layer and near wake about a double circular arc, compressor blade in cascade. The measurements were made at a chord Reynolds number of 500,000. Boundary layer measurements on the pressure surface indicate a transition region over the last 40% of the chord. A small separation bubble near the leading edge of the suction surface results in an immediate transition from laminar to turbulent flow. The non-equilibrium turbulent boundary layer separates near the trailing edge of the suction surface. Similarity of the outer region of the turbulent boundary layer ceases to exist in the separated region. Also, similarity does not hold in the near-wake region, a region which includes negative mean velocities because of the separation near the trailing edge on the suction surface

The boundary layer on compressor cascade blades

The characteristics of the flow field about highly loaded turbocompressor blades in a cascade wind tunnel were investigated. Experimental tests were conducted at chord Reynolds number (R sub c) near 500,000. A laser Doppler anemometer was employed in flow velocity measurement. Suction surface mean velocity and turbulence intensity profiles at a single incidence angle are presented. These data contribute to further understanding of two-dimensional boundary layer profiles, points of separation, and transition zones for turbomachine blades, and concomitantly, to compressor cascade predictive models

The boundary layer on compressor cascade blades

The flow field about an airfoil in a cascade at chord Reynolds number (R sub C) near 50,000. The program is experimental and combines laser Doppler anemometry (LDA) with flow visualization techniques in order to obtain detailed flow data (e.g., boundary layer profiles, points of separation and the transition zone) on a cascade of highly-loaded compressor blades. The information provided is to serve as benchmark data for the evaluation of current and future compressor cascade predictive models, in this way aiding in the compressor design process. The completed pressure surface mean velocity profiles, as well as two detailed near wake velocity profiles, all at a single incidence angle are provided

Prospective job analysis for the next pilot generation

To accomodate the expected growth of air traffic over the next two decades new operational concepts are currently under development, which will affect to some extent the job tasks and responsibilities of pilots and air traffic controllers. How will the operators perform in their potential new roles? Can we presume that they will easily be re‐trainable? Or will the job profile change to such an extent that it has to be considered already during the selection of the most suitable candidates? Especially for ab‐initio pilot and controller candidates selection decisions imply predictions of human performance for a longterm future. Therefore, a prospective analysis of job requirements is necessary to make sure that the selection battery is aligned with future roles and tasks. DLR has developed a simulation platform called AviaSim, which allows for low‐fidelity human‐in‐the‐loop simulations of potential future job tasks for pilots and controllers. Future scenarios are based on reviews of NextGen and SESAR concept papers and as well on “future workshops” with present job holders. In AviaSim we can examine the behavior of air traffic controllers working together in one scenario with up to eight pilots and additional experimental traffic. With eye‐gaze measurement, questionnaires and cognitive task interviews performance was analyzed in one en‐route and an arrival scenario. According to preliminarily findings future operators will need a higher degree of competence for operational monitoring, distributed teamwork, and time‐based operations. The simulation platform and the experimental setups are discussed in the paper