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The purpose of this paper is to present the results of the preliminary design and optimization of the air-intake system and the engine nacelle. The work was conducted as part of an integration process of a turboprop engine in a small aircraft in a tractor configuration.

The preliminary design process was performed using a parametric, interactive design approach. The parametric model of the aircraft was developed using the PARADES™ in-house software. The model assumed a high level of freedom concerning shaping all the components of aircraft important from the point of view of the engine integration. Additionally, the software was used to control the fulfillment of design constraints and to analyze selected geometrical properties. Based on the developed parametric model, the preliminary design was conducted using the interactive design and optimization methodology. Several concepts of the engine integration were investigated in the process. All components of the aircraft propulsion system were designed simultaneously to ensure their compliance with each other.

The concepts of the engine integration were modified according to changes in the design and technological constraints in the preliminary design process. For the most promising configurations, computational fluid dynamics (CFD) computations were conducted using commercial Reynolds-averaged Navier–Stokes solver FLUENT™ (ANSYS). The simulations tested the flow around the nacelle and inside the air-delivery system which consists of the air-intake duct, the foreign-particles separator and the auxiliary ducts delivering air to the cooling and air-conditioning systems. The effect of the working propeller was modeled using the Virtual Blade Model implemented in the FLUENT code. The flow inside the air-intake system was analyzed from the point of view of minimization of pressure losses in the air-intake duct, the quality of air stream delivered to the engine compressor and the effectiveness of the foreign particles separator.

Based on results of the CFD analyses, the final concept of the turboprop engine integration has been chosen.

The presented results of preliminary design process are valuable to achieve the final goal in the ongoing project.

The propulsion system integration of a turboprop aircraft, which has been developed for the basic trainer, was performed. The proper turboprop engine was selected among worldwide existing engines by the specific developed engine selection technique and trade‐off studies such as customer’s request for operational capability (ROC), propulsion system parameters, performance analysis with engine installed effects, future growth potential, integrated logistic support (ILS), maintainability, interfaces with the airframe, etc. The chin type air inlet with the plenum chamber was designed in consideration of the inclined configuration to minimize the propeller swirl effect, the inertial separation bypass device to reduce FOD, and the super‐ellipse and NACA‐1 profile lip to maximize the ram recovery. The air inlet was analyzed by a higher‐order source panel method considering propeller wake. The exhaust duct was designed through internal cross‐section area determination to maximize the cruising power as well as external configuration to maximize the effective power, to minimize the aerodynamic drag and to minimize the cockpit contamination by the exhaust gas. The proper oil cooler for the selected turboprop engine was determined with cooling requirements and the oil cooling inlet duct with NACA configuration was designed. The test of the propulsion system including the installation performance test with the effects of the air inlet, the exhaust duct, the propeller and the nose fuselage configuration was performed in the test cell.

The paper aims to present a way of engine model integration, an aircraft (multitask) and the mission into the single model that allows to study, from the level of selection of the engine cycle parameters, the feasibility of a specific mission with the assumed aerodynamic characteristics exemplified by a multitask airplane.

There were introduced dimensionless geometric and energetic criteria, binding parameters of the engine and the airplane. The following models were built: of the turbofan engine and the aircraft movements with the application of these criteria, creating a dimensionless model allowing for measuring the impact of engine design parameters on the efficiency of the mission undertaken.

The results were limited to the presentation of the impact of circuit parameters, such as engine TIT, OPR, BR on the defined criteria. The application of dimensionless criteria reduced the dimension of the task.

The presented method can be useful for engineers involved in the task of engine integration and the airplane at the preliminary design stage.

The originality of the presented solutions is reduced to provide a different, unconventional approach to the design process and not (so far) the engine itself but the entire aviation system.

The purpose of this paper is to present application of multidisciplinary design optimisation (MDO) in redesign of a small composite aircraft. The redesign process was integration of the turboprop engine in a small composite aircraft. The process requires cooperation of specialists from many disciplines and definition of their tasks. For selected tasks, the authors present results of the calculation.

The authors used collaborative optimisation (CO) algorithm to solve the problem. They decomposed this complex process into a set of tasks in different engineering/research disciplines and used techniques and methods specific for each task (research/engineering discipline) to find a proper solution. The computer-aided design (CAD), computational fluid dynamics (CFD) and computational structural mechanics (CSM) commercial software were used as common tools as well as intentionally developed computer programmes were used as basic tools in some tasks, in particular, for aerodynamic optimisation, calculation of load and stability of aircraft. The exchange of data between separate tasks allowed achieving the main goal of complex design process.

Selected optimisation algorithm, CO, proved efficient for the authors’ purposes. The effectiveness of multidisciplinary optimisation depends as much on organisational parameters as it does on technical and technology parameters.

Multidisciplinary optimisation needs to be an integral part of analysis and design process. The successful optimisation results allowed to meet the requirements and to proceed to the next phase of work – preparing technical documentation for manufacturing the components necessary for integration of the airplane with the new engine.

Presented results of design process are a valuable example of how to achieve the final goal in an ongoing project.

The purpose of this paper is to provide useful insights underlying the popularity of search engine technologies within a social media-intensive environment.

The degree of social interaction for social media platforms that integrate search engine technologies as part of the homepage and related experience is very mixed on part of its users. Through Barnard’ theory of authority acceptance, social media and its popularity may be examined by the ability of its users to create effective messages that can be broadcasted to many, yet controlled by individual. The hypotheses tested the interaction of social media and search engine with gender and technological ease-of-use factors.

The statistical evidence suggested that significant technological and ease-of-use aspects of search engines are not meaningful, based on gender alone. Males may slightly be prone to take advantage of such technologies, but their search and use patterns are not much varied from their female counterparts. Social media, generally more fully captured authority in individual search patterns, and a number of interactions among gender status, search engine characteristics, and social media were found to be significant and profound. The testing of these hypotheses directly reflect the complexities of unique needs among users of search engines within a social media environment.

Search engine technologies with a social media context has allowed for the development of a modern, user-driven internet experience that has been powered by users’ imagination and is designed to at least partially satisfy users’ need for self-directed engagement. Organizations are well advised to provide a mindful, less controlled, and more interactive presence of potential users, especially through an increasingly mobile presence.

Individuals as well as organizations are rapidly discovering that it is becoming easier to share and distribute their content, especially for more creative and innovative content, among all of its users. As businesses continue to focus on the quality of one’s own content, individuals are increasingly taking advantage of some tools to exert more control over their experiences and what they are willing to share, resulting in more user-based partnerships will formulate. As the transition of traditional forms of marketing to newer forms of integrated marketing, the future for search engines as marketing tools by social media users appears to be very promising in adding contextual content within users’ homepage.

This paper aims to set up and assess a new method to collaboratively mature the requirements for engine development in a more efficient way during the preliminary design phase.

A collaborative process has been set up in which detailed information on the behaviour of designed engines has been integrated into the aircraft preliminary sizing process by means of surrogate modelling.

The engine surrogate model has been invoked as a black box from within the aircraft preliminary design optimisation loops. The surrogate model reduces the uncertainty of coarse-grain formulas and may result in more competitive aircraft and engine designs. The surrogate model has been integrated in a collaborative cross-organisational workflow between aircraft manufacturer, engine manufacturer and simulation service providers to prepare for its deployment in industrial preliminary design processes.

The new collaborative way of working between aircraft manufacturer, engine manufacturer and simulation service providers could contribute to remove time consuming rework cycles in early and later design stages within delivering the optimal aircraft-engine combination.

The assessed process, based on an innovative collaboration standard, provides the opportunity to introduce useful design iterations with much more enriched information than in the classical design process as performed today. Specifically, the application of an engine surrogate model is advantageous, as it allows for extensive trade-off studies on aircraft level because of the low computational effort, while the intellectual property of the engine manufacturer (the engine preliminary design process) is respected and kept in-house.

To design an efficient and integrated framework for automated and simple data acquisition and processing targeted for first response scenarios.

Utilizes existing software/hardware integration tools and primarily off‐the‐shelf components. Use the modular system architecture for development of new applications. System construction is preceded by the analysis of currently available devices for specific data acquisition and processing.

The development and integration of data acquisition and processing tools for first responder scenarios can be rapidly achieved by the modular and already existing software/hardware integration platform. Data types processed by this system are biometrics, live video/audio and textual/command data. The data acquisition is followed by the prompt dissemination of information from the incident scene thus overcoming interoperability issues.

Integration of new modules is achieved through simple system upgrades – new applications are created and integrated while the rest of the platform remains intact. Off‐the‐shelf components used eliminate the need for specialized hardware development. The speech user interface allows simple interaction with the system in an eyes‐off, hands‐off manner.

The system represents an efficient platform for integrated data acquisition and processing specially targeted for first response. The test‐bed flexibility allows for straightforward integration of devices/applications handling new data type as required by the user.

Development or upgradation of airplanes requires many different analyses, e.g. thermal, aerodynamic, structural and safety. Similar studies were performed during configuration change design of commuter category aircraft equipped with pusher turboprop engines. In this paper, thermo-fluid analyses of interactions of the new propulsion system in tractor configuration with selected elements of airplane skin are carried out. This study aims to check the airplane skin material, and its geometry, including the Plexiglas passenger window material degradation, due to hot exhaust gas plume impingement. The impact of change in exhaust stub angle and asymmetric inboard-outboard stubs on the jet thrust at various flight operating conditions like minimum off-route altitude and cruise performance is assessed.

Commercial software-based numerical models were developed. In the first stage, heat and fluid flow analysis was performed over a twin-engine airplane’s nacelle, wing and center fuselage with its powerplant mounted in the high wing configuration. Subsequently, numerical simulations of thermal interactions between the hot exhaust gases, which leave the exhaust system close to the nacelle, flaps and the center fuselage, were estimated for various combinations of exhaust stub angles with asymmetry between inboard-outboard stubs at different airplane configurations and operating conditions.

The results of the simulations are used to recommend modifications to the design of the considered airplane in terms of material selection and/or special coatings. The importance and impact of exhaust jet thrust on the overall aircraft performance are investigated.

The advanced numerical model for the exhaust jet-airplane skin thermal interaction was developed to estimate the temperature effects on the propeller blades and aircraft fuselage surfaces during different flight operating conditions with multiple combinations of stub orientations.

THE Combustion and Propulsion Panel of A.G.A.R.D. (Advisory Group on Aeronautical Research and Development to N.A.T.O.) held its third Colloquium at Palermo, Sicily, during the period March 17–21, 1958. Nearly 200 delegates attended the Colloquium representing 10 different N.A.T.O. countries. There were 19 delegates from the U.K. and 12 of these participated either as authors, reviewers of papers or to the discussion. During the five‐day period, 18 invited papers were presented with prepared comments from 45 selected reviewers.