Multi-Fidelity Design Optimization of a Long-Range Blended Wing Body Aircraft with New Airframe Technologies

Karpuk, Stanislav; Liu, Yaolong; Elham, Ali

doi:10.3390/aerospace7070087

Cited by 26 publications

(23 citation statements)

References 31 publications

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“…For the short-range aircraft, such novel features are a hybrid laminar flow control in combination with structural weight reductions and an full electric propulsion system [59]. As a promising candidate for long-range aircraft, Blended Wing Bodies are studied, as well featuring novel concepts, such as laminar flow control, active load alleviation and boundary layer ingestion [60].…”

Section: Discussionmentioning

confidence: 99%

Environmental Noise Assessment of Holding Approach Procedures Using a Multi-Level Simulation Framework

et al. 2022

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Computational models of sufficient quality are indispensable to quantitatively assess aircraft noise reduction measures. Within this study, a multi-level simulation framework is established in order to predict the environmental noise of holding approach procedures by coupling simulation models from three different domains: flight performance calculation employing the base of aircraft data (BADA), jet engine performance using the software Gasturb and aircraft noise simulations based on the software sonAIR. Two different concepts of holding approach procedures are investigated, namely, the vertical holding stack and the linear hold point merge. The study is conducted considering generic air traffic scenarios at a single-runway airport. Thereby, the investigated air traffic is based on a statistical analysis of traffic data at existing airports and thus assumed to be representative. As the aircraft’s noise emission depends on both the aircraft and the engine performance, reliable results can be expected only if all individual challenges and interdependencies are accounted for simultaneously. Addressing this challenge is the main contribution of the presented work. The presented results show the plausibility of the proposed multi-level simulation framework, thus supporting its use to investigate the environmental noise impact of air traffic scenarios.

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Section: Discussionmentioning

confidence: 99%

Environmental Noise Assessment of Holding Approach Procedures Using a Multi-Level Simulation Framework

et al. 2022

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“…Karpuk et al [5] developed a design approach with a different fidelity level for a fuel-efficient BWB aircraft. The multi-fidelity aerodynamic was based on an AVL tool for low-fidelity levels while SU2 coupled to the FFD approach to change geometry was adopted for high fidelity computations.…”

Section: Related Workmentioning

confidence: 99%

“…The aerodynamic advantage of the BWB design relies on its lower wetted area to volume ratio and its Sears-Haack like body cross sections [4]. The BWB design provides a lower skin friction drag and a lower interference drag, driving to an increase of aircraft aerodynamic efficiency [5]. Additionally, because of the smoother wing-fuselage integration, it allows for increasing the passenger transport capabilities.…”

Section: Introductionmentioning

confidence: 99%

“…In the recent years, BWB design is reconsidered because of the strict mandatory reduction of NO x and CO 2 emissions required for aircraft industries. In this framework, it is worth emphasizing the activities of the German Cluster for Sustainable and Efficient Energy Aviation [5]. The program is actually aimed at finding mutual influence between brand new aircraft configurations and the development of new technologies over atmospheric emissions.…”

Section: Introductionmentioning

confidence: 99%

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Low Speed Aerodynamic Analysis of the N2A Hybrid Wing–Body

et al. 2022

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Reduction of atmospheric emissions is currently a mandatory requirement for aircraft manufacturers. Several studies performed on Blended Wing–Body configurations showed a promising capability of reducing fuel consumption by increasing, at the same time, passengers’ transport capabilities. Although several aerodynamic studies are available at transonic speeds, low-speed evaluations of aerodynamic performances of Blended Wing Body aircrafts are less investigated. In this framework, the present paper deals with the aerodynamic performance of the N2A aircraft prototype at low-Mach number conditions. Aircraft longitudinal aerodynamics is addressed at M∞=0.2 with steady state three-dimensional RANS simulations carried out at two Reynolds numbers equal to 6.60×106 and 1.27×108, respectively. The former refers to an experimental test campaign performed at NASA Langley 14-by-22 foot subsonic tunnel, while the latter is related to free-flight conditions close to an approach and landing phase. Flowfield simulations are performed using the Computational Fluid Dynamic code FLUENT and the SU2 open-source code, currently adopted for research applications. Numerical solutions are validated by using available experimental data with reference to lift, drag, pitching moment and drag polar estimations. Pre-stall and post-stall aerodynamic behaviour through mean flow-field visualization along with the comparison of pressure distributions at several AoAs is addressed. Furthermore, the effect of convective discretization on a numerical solution for SU2 is discussed. Results indicate a good agreement with available experimental predictions. The present study aims to bridge existing computations at a Eulerian low-Mach number, with RANS computations and constitutes a further test-case for SU2 code with respect to a full aircraft configuration.

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“…The study used a forward-swept wing configuration with an 80% laminar flow wing and a 70% laminarised fuselage. Karpuk et al performed an aircraft design and performance analysis for a blended wing body configuration with BLS [19]. They used multi-fidelity aircraft design code SUAVE with a connection to high-fidelity computational fluid dynamics (CFD) code SU2 but simulating the active flow control with low-fidelity model.…”

Section: Introductionmentioning

confidence: 99%

Multidisciplinary design optimisation of a fully electric regional aircraft wing with active flow control technology

et al. 2021

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The German research Cluster of Excellence SE2A (Sustainable and Energy Efficient Aviation) is investigating different technologies to be implemented in the following decades, to achieve more efficient air transportation. This paper studies the Hybrid Laminar Flow Control (HLFC) using boundary layer suction for drag reduction, combined with other technologies for load and structural weight reduction and a novel full-electric propulsion system. A multidisciplinary design optimisation framework is presented, enabling physics-based analysis and optimisation of a fully electric aircraft wing equipped with HLFC technologies and load alleviation, and new structures and materials. The main focus is on simulation and optimisation of the boundary layer suction and its influence on wing design and optimisation. A quasi three-dimensional aerodynamic analysis is used for drag estimation of the wing. The tool executes the aerofoil analysis using XFOILSUC, which provides accurate drag estimation through boundary layer suction. The optimisation is based on a genetic algorithm for maximum take-off weight (MTOW) minimisation. The optimisation results show that the active flow control applied on the optimised geometry results in more than 45% reduction in aircraft drag coefficient, compared to the same geometry without HLFC technology. The power absorbed for the HLFC suction system implies a battery mass variation lower than 2%, considering the designed range as top-level requirement (TLR).

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Multi-Fidelity Design Optimization of a Long-Range Blended Wing Body Aircraft with New Airframe Technologies

Cited by 26 publications

References 31 publications

Environmental Noise Assessment of Holding Approach Procedures Using a Multi-Level Simulation Framework

Environmental Noise Assessment of Holding Approach Procedures Using a Multi-Level Simulation Framework

Low Speed Aerodynamic Analysis of the N2A Hybrid Wing–Body

Multidisciplinary design optimisation of a fully electric regional aircraft wing with active flow control technology

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