Civil aviation and the environment – the next frontier for the aerodynamicist

Green, J. E.

doi:10.1017/s0001924000001378

Cited by 36 publications

(30 citation statements)

References 17 publications

(21 reference statements)

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“…This LTO cycle is representative of a typical commercial aircraft operation as it 8 T HE AERONAUTICAL JOURNAL JANUARY 2012 descends from 3,000ft on its approach path to the time it attains the same altitude during take-off (35) and is detailed in Table 1.…”

Section: Emissionsmentioning

confidence: 99%

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Aircraft conceptual design for optimal environmental performance

Henderson

Martins

Perez

2012

Aeronaut. j. (1968)

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Consideration of the environmental impact of aircraft has become critical in commercial aviation. The continued growth of air traffic has caused increasing demands to reduce aircraft emissions, imposing new constraints on the design and development of future airplane concepts. In this paper, an aircraft design optimisation framework is used to design aircraft that minimise specific environmental metrics. Multidisciplinary design optimisation is used to optimise aircraft by simultaneously considering airframe, engine and mission. The environmental metrics considered in this investigation are CO 2 emissions -which are proportional to fuel burn -and landingtakeoff NO x emissions. The results are compared to those of an aircraft with minimum direct operating cost. The design variables considered in the optimisation problems include aircraft geometry, engine parameters, and cruise settings. An augmented Lagrangian particle swarm optimiser and a genetic algorithm are used to solve the single objective and multi-objective optimisation problems, respectively.

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Section: Emissionsmentioning

confidence: 99%

“…These improvements have been achieved by the development of technologies that increase engine efficiency, reduce airframe drag and structural weight, and streamline air traffic (7)(8)(9) . Because of these improvements, fuel burn per passenger-mile has been reduced by more than 70% since the early 1960s (2,7) .…”

Section: Introductionmentioning

confidence: 99%

Aircraft conceptual design for optimal environmental performance

Henderson

Martins

Perez

2012

Aeronaut. j. (1968)

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“…F UEL economy is, now more than ever, of paramount importance for the aeronautical industry [1]. Not only do fuel-efficient aircraft cost less to operate, but they also produce less emissions responsible for climate change.…”

Section: Introductionmentioning

confidence: 99%

Euler-Equation-Based Drag Minimization of Unconventional Aircraft Configurations

Gagnon

Zingg

2016

Journal of Aircraft

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This study investigates the potential of unconventional aircraft transports through numerical optimization. Three distinct configurations are investigated: a box wing, a C-tip blended wing-body, and a braced wing. Each transport is sized for the same regional mission and is subjected to the same optimization strategy based on the Euler equations. The figure of merit is inviscid pressure drag at transonic speed; the nonlinear constraints are lift, pitching moment, and internal volume. The design variables include the section shape and twist distribution of the main lifting surfaces. It is found that the box-wing, C-tip blended-wing-body, and braced-wing configurations investigated here are, respectively, 34.1, 36.2, and 40.3% more efficient than a similarly optimized conventional tube-and-wing configuration. Each optimization revealed, in one way or another, the importance of accounting for flow nonlinearity during the early stages of unconventional aircraft design. For the blended wing-body, the C tip does not appear to provide a drag benefit over a purely vertical winglet, presumably as a result of the compressibility effects prevalent in the C opening. For the braced wing, compressibility effects also lead to a curious result, where the supporting strut finds itself carrying negative lift at the optimum. Nomenclature= span efficiency L = lift, N n = normal force (section), m q ∞ = freestream dynamic pressure, N∕m 2 W = weight, N x, y, z = chordwise, spanwise, and vertical coordinates, m α = angle of attack, deg

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“…Therefore, other means of reducing greenhouse gas emissions at reasonable cost must be sought. 2 One such prospect is through improved fuel e ciency via drag and weight reduction aided by aerodynamic shape optimization 3 (ASO) and multidisciplinary design optimization (MDO), due to their potential for discovering novel, optimal aircraft configurations.…”

Section: Introductionmentioning

confidence: 99%

Two-Level Free-Form Deformation for High-Fidelity Aerodynamic Shape Optimization

Gagnon

Zingg

2012

12th AIAA Aviation Technology, Integration, and Operations (ATIO) Conference and 14th AIAA/ISSMO Multidisciplinary Analysis And

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A general and unified geometry framework based on non-uniform rational B-splines is presented. One key aspect of this framework is the use of free-form deformation where the control points defining the geometry itself are embedded rather than the usual surface grid points. This ensures that one maintains an analytical representation of the geometry as it deforms and, if required, also enables the use of an integrated algorithm for mesh movement. The flexibility and robustness of the proposed approach are demonstrated in the context of aerodynamic shape optimization by maximizing, using an Euler-based flow solver and gradient-based optimizer, the lift-to-drag ratio of an initially half-sphere-shaped geometry. Sensitivities are computed analytically via the discrete adjoint method.

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Civil aviation and the environment – the next frontier for the aerodynamicist

Abstract: † I am grateful to Peter Wong of ARA for providing these results, derived using the well validated BVGK aerofoil design code (44) as further developed at ARA to apply to aerofoils with suction.

Cited by 36 publications

References 17 publications

Aircraft conceptual design for optimal environmental performance

Aircraft conceptual design for optimal environmental performance

Euler-Equation-Based Drag Minimization of Unconventional Aircraft Configurations

Two-Level Free-Form Deformation for High-Fidelity Aerodynamic Shape Optimization

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