Aerodynamic Shape Optimization for Natural Laminar Flow Using a Discrete-Adjoint Approach

Rashad, Ramy; Zingg, David W.

doi:10.2514/6.2015-3061

Cited by 10 publications

(4 citation statements)

References 52 publications

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“…Therefore, the SWB N is optimized using the discrete adjoint method at Ma = 0:85, α = 1:5 °. The adjoint method provides a more efficient method of calculation gradients, which is independent of the step size and of the number of design variables [32].…”

Section: Improvement Of Swb Aerodynamic Designmentioning

confidence: 99%

Design Improvement of a BWB Aerodynamic Performance at Cruise and Take-Off Speeds

Duan

2022

International Journal of Aerospace Engineering

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As a high-performance aircraft, BWB (blended wing body) has attracted the attention of many countries around the world. A 300-seat BWB design is proposed by the Airplane Concept Design Institute of Northwestern Polytechnical University, which is also called SWB. The aerodynamic performance of it is evaluated by CFD (computational fluid dynamics). The CFD calculation method is based on RANS (Reynolds-averaged Navier–Stokes), and it is verified by wind tunnel test results at take-off speed. However, the aerodynamic design of the SWB needs to be improved to meet the market demand to increase its cruise Mach number from 0.8 to 0.85. To achieve this goal, firstly, based on the previous calculation and analysis results, the basic shape of SWB is improved by using “aft-body extending” technology and discrete adjoint optimization method. Then, the winglets are applied to the improved basic shape to improve its cruise speed aerodynamic performance, and the Krueger flaps are applied as its high-lift device to improve its take-off and landing aerodynamic performance. The CFD calculation and wind tunnel test results show that these improvements make SWB-2 have a good aerodynamic performance at the Mach number of 0.85. Therefore, these design improvements are appropriate and effective for improving the aerodynamic performance of BWB.

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Section: Improvement Of Swb Aerodynamic Designmentioning

confidence: 99%

Design Improvement of a BWB Aerodynamic Performance at Cruise and Take-Off Speeds

Duan

2022

International Journal of Aerospace Engineering

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“…To reduce skin-friction drag, the main design philosophy is to ensure that the flow remains laminar for as large an area as possible [14]. Adjoint-based aerofoil optimisation is per- formed for natural laminar flow in [15], incorporating an iterative laminar-turbulent transition prediction methodology.…”

Section: Introductionmentioning

confidence: 99%

Wing-body junction optimisation with CAD-based parametrisation including a moving intersection

Timme

Mykhaskiv

et al. 2017

Aerospace Science and Technology

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Over the past decades significant progress has been made with adjoint computational fluid dynamics solvers, which are an essential part of efficient high-fidelity aerodynamic shape optimisation. Shape parametrisation is much less mature, in particular the field is lacking efficient and automatic CAD-based parametrisation methods. The paper proposes a novel CAD-based parametrisation with CAD in the design loop such that the CAD shape can ultimately serve as a datum surface in multidisciplinary optimisation. Wing and fuselage are modelled with B-spline surfaces. The intersection line is calculated using an in-house implementation of a B-spline surface modeller and its derivative is efficiently calculated via finite differences. The proposed parametrisation method is applied to the redesign of the wingfuselage junction of the DLR-F6 model using an adjoint solver based on Reynolds-averaged Navier-Stokes equations. The moving intersection line capability enables the fuselage surface to be deformed and the resulting intersection line to move along the fixed wing during optimisation. The flow separation in the wing-body junction is substantially suppressed by an improved fuselage shape, at the cost of O(10) steady-state flow and adjoint solutions. The proposed parametrisation method represents an important step towards automated CAD-based optimisation for fully-featured aircraft characterised by complex intersecting surfaces.

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“…it does not require different formulations for turbulent subsonic, transonic, or supersonic flow. The extension of a discrete-adjoint framework for applications with flows with turbulent laminar transition is a current area of research (see Ref. 16 and references therein).…”

Section: Introductionmentioning

confidence: 99%

DLR transonic inverse design code, extensions and modifications to increase versatility and robustness

Streit¹,

Hoffrogge²

2017

Aeronaut. j.

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The DLR inverse design code computes the wing geometry for a prescribed target pressure distribution. It is based on the numerical solution of the integral inverse transonic small perturbation (TSP) equations. In this work, several extensions and modifications of the inverse design code are described. Results are validated with corresponding redesign test cases. The first modification concerns applications for high transonic Mach numbers or cases with strong shocks. The introduced modifications enable converged design solutions for cases where the original method failed. The second modification is the extension of the code to general non-planar wings. Previously, the design code was restricted to non-planar wing designs with small dihedral or to nacelle design. A third modification concerns aerofoil/wings designed for wind-tunnel design. In order to design a swept wing between two wind-tunnel walls, the solution method was extended to two symmetry planes. The introduced extensions and modifications have increased the robustness and range of applicability of the inverse design code.

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Aerodynamic Shape Optimization for Natural Laminar Flow Using a Discrete-Adjoint Approach

Cited by 10 publications

References 52 publications

Design Improvement of a BWB Aerodynamic Performance at Cruise and Take-Off Speeds

Design Improvement of a BWB Aerodynamic Performance at Cruise and Take-Off Speeds

Wing-body junction optimisation with CAD-based parametrisation including a moving intersection

DLR transonic inverse design code, extensions and modifications to increase versatility and robustness

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