Conceptual Design Trade Study for an Energy-Efficient Mid-Range Aircraft with Novel Technologies

Karpuk, Stanislav; Elham, Ali

doi:10.2514/6.2021-0013

Cited by 22 publications

(24 citation statements)

References 27 publications

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“…With regards to engine integration with BLI and according Power-Saving-Coefficients (PSC) the aft fuselage PSC can be predicted with low uncertainty in the range of 5-8% while the over-the-wing engine is affected by a more sensitive tradeoff between wing and engine aerodynamics which can also lead to a pylon mounted solution as the more robust result. The MDO study on both configurations of the mid-range aircraft shows that the forward-swept wing configuration is more efficient in terms of energy consumption [36]. Table 2 summarizes the characteristics of both forward-and backward-swept wing aircraft in direct comparison with to the Airbus A320.…”

Section: Preliminary Results On Overall Aircraft Levelmentioning

confidence: 99%

Vehicle Technologies towards Sustainable and Energy Efficient Aviation

Friedrichs

Elham

Hühne

et al. 2022

AIAA SCITECH 2022 Forum

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The overall mission is research and fundamental technological development for a sustainable future global air transport system. Following the vision of zero fossil fuel usage in aviation in a 2050 timeframe, reducing material and noise emissions while keeping air transport affordable on short to long range missions, SE²A focuses on significantly reducing the aircraft energy demand in combination with future energy storage and conversion technologies. This large design space makes preliminary system design and assessment based on models of different fidelity level indispensable. In this paper, the framework and research structure of the Cluster is described as well as a special focus on relevant and required vehicle technologies. This follows the need for a significant reduction of the mission energy to allow for future alternative propulsion systems and covers means for radical reductions in aircraft drag and dynamic loads, which in turn allow for reduced operating empty weight. An overall aircraft design methodology is employed for integration and assessment of technological progress. Such analysis is used to identify and quantify snowball effects and to prioritize technologies, but also to identify conflicting areas and requirements.

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Section: Preliminary Results On Overall Aircraft Levelmentioning

confidence: 99%

Vehicle Technologies towards Sustainable and Energy Efficient Aviation

Friedrichs

Elham

Hühne

et al. 2022

AIAA SCITECH 2022 Forum

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“…The aircraft without novel technologies assumed 45% laminar flow on the wing and empennage, 5% laminar 18 Figure 1. SE²A short range all-electric aircraft [2] Figure 1 shows the SE²A 1 short range (SR) aircraft with foldable wings and a high aspect ratio. The SE²A SR version 1 (SRV1) features an all-electric propulsion system with two fuselage-mounted electric motor-driven propellers.…”

Section: Sensitivity Analysis Of the Aircraft Characteristics To Tech...mentioning

confidence: 99%

“…The SE²A SR version 1 (SRV1) features an all-electric propulsion system with two fuselage-mounted electric motor-driven propellers. Concerning the battery energy, a cell energy density of 800Wh/kg was assumed to be reached by the year 2050 [1].…”

Section: Sensitivity Analysis Of the Aircraft Characteristics To Tech...mentioning

confidence: 99%

Approach for CO2 Emission Related Cost Functions in the Context of Trade-Off Investigations of a Future Energy Efficient European Aviation

Forster¹,

Yildiz²,

Feuerle³

et al. 2022

Preprint

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Aircraft emissions represent a relevant amount of human induced CO2. Globally, up to 2.5 per cent of such emissions stem from the aviation industry. In order to investigate the effects within the atmosphere, realistic flight profiles are necessary to provide quantitatively tangible values of emissions. The flight profiles and the according fuel consumption can be calculated by using waypoints from flight plans and Base of Aircraft Data (BADA). This paper presents an approach to refine the fuel consumption by integrating the passenger load into the calculation. Since effects of emissions have to be assessed on a greater scale, such as on the European air traffic network, the presented approach provides cost functions for CO2 emissions for different aircraft types and load factors. The cost functions were derived by means of regression analyses of BADA based calculated flight profiles with a step size of one second. The calculations are based on real historic traffic scenarios of several days. The derived aircraft specific fuel burn coefficients enable a simple and efficient integration of CO2 estimations depending on the flight distance, load factor and aircraft type. This can be applied to large traffic scenarios to also study different set-ups such as travel restrictions, other disruptions or an alteration in the traffic system as a whole. In order to enable the assessment of further aspects of such changes to the European air traffic system at large and to foster reproducibility and comparability of related studies, we provide further general-purpose cost estimation functions for several important key characteristics. Besides fuel consumption, we develop cost estimations for air navigation fees and maintenance for conventional aircraft. Those functions are also provided for the design concept of a short-range all-electric aircraft. This propeller aircraft features game-changing technologies such as active laminar flow control, active load alleviation and advanced materials and structure concepts. The approaches discussed in this paper will focus on the generic aspects of aircraft related costs, which can be derived from general available data. For the sake of reproducibility, the results will be made publicly available.

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“…In this study, we consider version 2 of the DFG Cluster of Excellence "Sustainable and Energy Efficient Aviation" (SE 2 A) mid range passenger aircraft, depicted in Figure 3. Its conceptual design is outlined in [11]; for more details refer to Section 4.3. As opposed to a conventional mid-range aircraft with a twin-engine podded configuration, this aircraft features a fuselage tail mounted engine as well as two on-wing engines.…”

Section: Boundary Layer Ingestionmentioning

confidence: 99%

“…The aircraft has a maximum takeoff weight of 69,000 kg, a design range for maximum payload of 3981 km, and 51.57 m wing span with an aspect ratio of 16. For details of the design please refer to [11].…”

Section: Reference Configurationmentioning

confidence: 99%

Development of a Multi-Segment Parallel Compressor Model for a Boundary Layer Ingesting Fuselage Fan Stage

Voigt

Friedrichs

2021

Energies

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The present methodological study aims to assess boundary layer ingestion (BLI) as a promising method to improve propulsion efficiency. BLI utilizes the low momentum inflow of the wing or fuselage boundary layer for thrust generation in order to minimize the required propulsive power for a given amount of thrust for wing or fuselage-embedded engines. A multi-segment parallel compressor model (PCM) is developed to calculate the power saving from full annular BLI as occurring at a fuselage tail center-mounted aircraft engine, employing radially subdivided fan characteristics. Applying this methodology, adverse effects on the fan performance due to varying inlet distortions depending on flight operating point as well as upstream boundary layer suction can be taken into account. This marks one step onto a further segmented PCM model for general cases of BLI-induced inlet distortion and allows the evaluation of synergies between combined BLI and active laminar flow control as a drag reduction measure. This study, therefore, presents one further step towards lower fuel consumption and, hence, a lower environmental impact of future transport aircraft.

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Conceptual Design Trade Study for an Energy-Efficient Mid-Range Aircraft with Novel Technologies

Cited by 22 publications

References 27 publications

Vehicle Technologies towards Sustainable and Energy Efficient Aviation

Vehicle Technologies towards Sustainable and Energy Efficient Aviation

Approach for CO2 Emission Related Cost Functions in the Context of Trade-Off Investigations of a Future Energy Efficient European Aviation

Development of a Multi-Segment Parallel Compressor Model for a Boundary Layer Ingesting Fuselage Fan Stage

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