1,720,975 research outputs found
Aerodynamic design of advanced rear end for large passenger aircraft
Full text linkThis paper focuses on the aerodynamic design of an advanced rear end concept for a large passenger aircraft, such as the Airbus A320. The aim was to reduce the size of the horizontal tailplane to minimize the aerodynamic drawbacks related to longitudinal stability and control requirements. This reduction would lead to improved aircraft performance by reducing fuel burn and rear-end weight. Assuming the same position of the aerodynamic center of the horizontal tailplane of a conventional aircraft, the results of this investigation showed that the required stabilizing performance of the tail could be achieved with a smaller tail surface. A reduction of 6% in tail planform area was achieved by leveraging the unique aerodynamic characteristics of a forward-swept tail, combined with the implementation of a leading-edge extension device. The reduced wetted area and the lower weight of the horizontal empennage could result in fuel savings of 100 to 120 kg of fuel per 1,000 km. This is equivalent to approximately 1.0 to 1.2% for the specific aircraft category being considered. © 2023, Association of American Publishers. All rights reserved
Beyond conventional: An integrated aerostructural optimization approach for innovative tailplane configurations
No full textRetrofitting Cost Modeling in Aircraft Design
Full text linkAircraft retrofitting is a challenging task involving multiple scenarios and stakeholders. Providing a strategy to retrofit an existing platform needs detailed knowledge of multiple aspects, ranging from aircraft performance and emissions, development and conversion costs to the projected operating costs. This paper proposes a methodology to account for retrofitting costs at an industrial level, explaining the activities related to such a process. Costs are mainly derived from three contributions: development costs, conversion costs and equipment acquisition costs. Different retrofitting packages, such as engine conversion and onboard systems electrification, are applied in the retrofitting of an existing 90 PAX regional turbofan aircraft, highlighting the impact on both aircraft performance and industrial costs. Multiple variables and scenarios are considered regarding trade-offs and decision-making, including the number of aircraft to be retrofitted, the heritage of an aircraft and its utilization, the fuel price and the airport charges. The results show that a reduction of 15% in fuel demand and emissions are achievable, considering a fleet of 500 platforms, through a conspicuous investment of around EUR 20 million per aircraft (50% of the estimated price). Furthermore, depending on the scenarios driven by the regulatory authorities, governments or airlines, this paper provides a useful methodology to evaluate the feasibility of retrofitting activities
IMPACT - Aircraft advanced rear end and empennage optimisation enhanced by anti-ice coatings and devices.
No full textThe research project is a 36-months project started in September 2020 and coordinated by AIT (Austrian Institute of Technology). IMPACT tackles all the challenges of the call “Rear fuselage and empennage shape optimization including antiicing technologies” by unlocking the capability to perform fast and accurate 3D ice accretion simulation suitable for non-straight leading-edge empennages, accounting for effects of passive anti-ice coatings and devices like leading-edge undulations, by characterising, integrating, and exploiting the passive anti-ice coatings and devices for non-straight leading-edge empennage configurations, reaching TRL 5 at the end of the project and by developing and applying innovative aerostructural optimisation methods for advanced rear ends (ARE), including the effects of the passive antiice coatings and devices, to minimise drag and include structural and aeroelastic constraints. The project will validate the accuracy of the 3D icing accretion simulations and the performance of passive anti-ice coating and devices by means of large scale icing wind tunnel (IWT) experimental tests. IMPACT will ultimately support Airbus’ progress with the advanced rear end concept, enhancing the competitiveness of the European LPA industry and value chain. IMPACT Partners are AIT, CEST, ANSYS Canada, EUROTECH company, University of Southampton, etc. and AIRBUS is the topic leader
Powertrain Model Improvement for Hybrid-Electric Regional Aircraft
No full textThis paper deals with the definition of an improved powertrain model for hybrid-electric aircraft. It is well known that powertrain equations are one of the most convenient tools for modelling the propulsion system at aircraft level, when it comes to hybrid architectures characterized by more than a single propulsive source. However, for a reliable implementation of a robust optimization algorithm for the hybridization parameters, the designer should consider some singularity points related to certain non-physical configurations depending on the operating mode. In this work, singularities are firstly identified by analyzing the operating modes, then a solving strategy is reported. Another crucial aspect is the correct design and simulation of battery behavior. In a broader perspective, the high-level objective of the activities related to powertrain model is to assess a possible fuel saving for regional turboprops using e-storage units as secondary power source. In this respect, preliminary results in terms of flight performance referred to a regional aircraft similar to ATR42 are presented and discussed. The authors conclude that a block fuel saving up to 51% for the typical mission is possible with a battery specific energy of 500 Wh/kg and when the benefits of aero-propulsive interaction are fully exploited
Aerodynamics characteristics of an innovative large turboprop through wind tunnel tests including propulsive effects
No full textThis paper deals with the assessment of both longitudinal and directional aerodynamic characteristics of an innovative large capacity turboprop aircraft by means of a wind tunnel test campaign on a scaled model. The aircraft under investigation is an innovative turboprop platform providing for a three lifting surface layout and a rear engine installation. The scope of this research is to deeply investigate the aerodynamic behavior of such an innovative platform to assess the aerodynamic interferences among the aircraft components. In particular, the effects of the third lifting surface (the canard), installed in front of the main wing, must be carefully investigated to have a reliable estimate of the aircraft stability and controllability characteristics. This innovative platform provides for a rear engine installation at the tip of the horizontal tailplane. Thus, a specific experimental campaign has been dedicated to investigating the aircraft aerodynamic characteristics in power on conditions
TECHNOLOGY ROADMAP AND CONCEPTUAL DESIGN OF HYBRID AND ELECTRIC CONFIGURATIONS IN THE COMMUTER CLASS
Full text linkThe growing sensitivity to the problem of sustainability requires a rethinking of how aviation is typically conceived by modern society. The aim of the research today must be to analyze the feasibility of disruptive solutions, which drastically reduce consumption and make it possible to meet the growing demand in the commercial aviation sector. The current level of technological maturity does not allow direct implementation on large commercial aircraft, which are responsible for most of the emissions from aviation. In this context, the Clean Sky 2 ELICA project aims to trace a technological roadmap towards green aviation, using the Small Air Transport as a test bed. Two different 19-seat commuter aircraft are presented in this work. The first one, with entry into service in 2025, presents a hybrid-electric architecture with batteries. The second configuration, with entry into service in 2035, is entirely propelled with hydrogen fuel cells, allowing the direct emissions of carbon and nitrogen oxides to be totally eliminated. Both configurations benefit from distributed electric propulsio
Development of new preliminary design methodologies for regional turboprop aircraft by CFD analyses
No full textSince 2011 the aerodynamic research group of the Dept. of Industrial Engineering of the University of Naples "Federico II" makes use of the University's computing grid infrastructure SCoPE to perform parallel computing simulations with the commercial CAE package Star-CCM+. This infrastructure allows Navier-Stokes calculations on complete aircraft configurations in a relative short amount of time. Therefore, the software and the above mentioned infrastructure allow the parametric analysis of several configurations that are extremely useful to the correct estimation of aerodynamic interference among aircraft components and to highlight some useful trends that could indicate how a specific aerodynamic characteristic (i.e. the drag of a component, the wing downwash or the directional stability contribution of the vertical tail) is linked to aircraft geometrical parameters. Thus, with the choice of a specific set of test-cases it is possible to make a deep investigation on some aerodynamic features and, from the analyses of results, it is possible to extract and develop ad-hoc semi-empirical methodologies that could be used in preliminary design activities.
In this paper, two investigations are presented: the aerodynamic interference among aircraft components in sideslip and the aerodynamic characteristics of a fuselage, focusing on typical large turbopropeller aircraft category
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