Advanced Tube and Wing Aircraft for Year 2050 Timeframe

Heinemann, Philipp; Panagiotou, Pericles; Vratny, Patrick C.; Kaiser, Sascha; Hornung, Mirko; Yakinthos, K.

doi:10.2514/6.2017-1390

Cited by 18 publications

(22 citation statements)

References 16 publications

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“…8 Applications of technology evaluation and selection in aircraft conceptual design are ubiquitous. 3,[9][10][11] This paper seeks answer to the question how technology evaluation and assessment is performed in the current state-of-the-art. Some critical remarks are provided that reflect the shortcomings of current stateof-the-art and possible areas of improvement.…”

Section: Introductionmentioning

confidence: 99%

Uncertainty-Based Design Optimization and Technology Evaluation: A Review

Roelofs

Vos

2018

2018 AIAA Aerospace Sciences Meeting

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Evaluation and assessment of novel technologies for aerospace applications is essential for business strategy and decision making regarding development efforts. Since technology is evaluated in the conceptual design phase and little is known about the technology, large uncertainty is present. This uncertainty needs to be accurately assessed and managed. To investigate the research efforts that have been performed to perform technology evaluation under uncertainty, a literature review was conducted, focusing on methods and modeling approaches to assign and quantify these uncertainties. It is found that probability theory is still the most popular theory for representing uncertainty. Polynomial Chaos Expansions and Stochastic Collocation methods are gaining popularity for propagating uncertainty through a modeling environment, but Monte Carlo Simulations are still widely used. Commonly, surrogate models are used to reduce computational effort. Other efforts focus on the use of multifidelity approaches to reduce computational effort when high-fidelity methods are required. Four issues that may need to be addressed in future research were identified.

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Section: Introductionmentioning

confidence: 99%

Uncertainty-Based Design Optimization and Technology Evaluation: A Review

Roelofs

Vos

2018

2018 AIAA Aerospace Sciences Meeting

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“…The drag reduction was mainly induced by the friction drag, while the pressure drag was increased. According to the empirical relation [29], the aerodynamic forces of an airfoil and a swept wing can be expressed as Equations (1)- (3). Λ is the sweep angle.…”

Section: Clsweep = Clairfoil Cos 2 λmentioning

confidence: 99%

“…Drag reduction is therefore one of the most important goals of aircraft design. The Flightpath 2050 perspective formulated by the Advisory Council for Aviation Research and Innovation in Europe aims to reduce the energy requirements of airframes and propulsion systems by 68% before 2050 (referenced to the year 2000) [3]. The aerodynamic drag must be greatly reduced to achieve this goal of 2050.…”

Section: Introductionmentioning

confidence: 99%

Study on Riblet Drag Reduction Considering the Effect of Sweep Angle

Zhang

Yin

2019

Energies

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This study computationally evaluates the riblet drag reduction effect considering the effect of sweep angle. An implicit large eddy simulation is performed on a channel flow and an infinite swept wing. First, three different inclined angles between the riblets and the flow direction are tested in the channel flow. The results show that with increases in the inclined angle, the friction drag decreases, while the pressure drag increases approximately quadratically. The riblets with a 30° inclined angle increase the total drag of the channel flow. Then, an infinite wing with a 30° swept angle with and without riblets is studied. The riblets demonstrate satisfactory drag reduction efficiency because the cross flow over most parts of the wing is mild. The lift and friction drag follow the relation of the cosine law of a swept wing. Moreover, the cross flow and the turbulence fluctuation are suppressed by the riblets.

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“…It is also assumed that the lift to drag ratio of the aircraft will improve and weight will be reduced, thanks to the introduction of higher-aspect-ratio carbon-fibre reinforced polymer wings, flyby-light systems, reduced-weight cabin furnishings, hybrid laminar flow control etc. [24].…”

Section: Fuel Burn Estimationmentioning

confidence: 99%

“…When the feasibility of the engine design configuration is benchmarked against the SRIA 2050 fuel-burn-reduction target of 68%, the reference 2050 GOR IP-drive engine misses the mark, but the optimistic design meets it [24]. Figure 20 compares the relative fuel-burn benefits derived from all three 2050 GOR IP-drive design cases, the SRIA fuel burn target, and the reference GOR 2050 engine design configuration, relative to a short-range turbofan in Y2000.…”

Section: Parametermentioning

confidence: 99%

Thermodynamic analysis of nutating disc engine topping cycles for aero-engine applications

Sebastiampillai

Rolt

Jacob

et al. 2019

Energy

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Within the next thirty years the evolutionary approach to aero engine development will struggle to keep abreast with increasingly stringent environmental targets. Therefore radical approaches to aeroengine development in terms of energy savings need to be considered. One particular concept involves the inclusion of a pressure-rise combustion system, within the architecture of an aero-engine, to provide additional shaft power. The nutating disc engine concept is a strong contender due to its power density. The feasibility of the nutating disc engine has been previously investigated for unmanned vehicle applications. However, this paper investigates the performance benefits of incorporating a nutating disc core in a larger geared open rotor engine for a potential entry in to service in 2050. In addition, a methodology is presented to estimate the size and weight of the nutating disc core. This methodology is pivotal in determining the overall performance of the novel aero-engine cycle. The outcome of this study predicts a potential 9.4% fuel burn benefit, over a state of the art geared open rotor in the year 2050. In addition, the sensitivity of the nutating disc design variables was explored. This showcases a pessimistic design and an optimistic design, showing the range of possible fuel burn benefits compared to a comparable year-2000 aircraft mission. Highlights • The nutating disc engine, is a power-dense internal combustion engine that claims high thermal efficiency. • This study investigates the benefit derived from integrating a Dual-cycle (Otto and Diesel) within a Brayton cycle. • A methodology to predict the size and weight of the nutating disc engine is presented. This is essential to determine aircraft mission level fuel burn benefits/penalties • When the nutating disc engine is integrated into the architecture of a year 2050 geared open rotor and aircraft, the potential fuel-burn benefit is 9.4% relative to a year 2050 baseline aircraft.

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Advanced Tube and Wing Aircraft for Year 2050 Timeframe

Cited by 18 publications

References 16 publications

Uncertainty-Based Design Optimization and Technology Evaluation: A Review

Uncertainty-Based Design Optimization and Technology Evaluation: A Review

Study on Riblet Drag Reduction Considering the Effect of Sweep Angle

Thermodynamic analysis of nutating disc engine topping cycles for aero-engine applications

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