Aerodynamic optimization and mechanism design of flexible variable camber trailing-edge flap

Lu, Weishuang; Tian, Yajie; Liu, Peiqing

doi:10.1016/j.cja.2017.03.003

Cited by 46 publications

(21 citation statements)

References 6 publications

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“…The question of finding the best calibration matrices Q x and Q t is a delicate one. First of all, the modes signs of sampling spatial and temporal bases must be adjusted with respect to a reference basis 5 . The reference basis denoted Φ γ k 0…”

Section: Description Of the Methodsmentioning

confidence: 99%

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Non intrusive method for parametric model order reduction using a bi-calibrated interpolation on the Grassmann manifold

Oulghelou

Allery

2019

Preprint

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Approximating solutions of non-linear parametrized physical problems by interpolation presents a major challenge in terms of accuracy. In fact, pointwise interpolation of such solutions is rarely efficient and leads generally to incorrect results. However, instead of using a straight forward interpolation on solutions, reduced order models (ROMs) can be interpolated. More particularly, Amsallem et al. [1] proposed an efficient POD (Proper Orthogonal Decomposition) reduced order models interpolation technique based on differential geometry tools. This approach, named in this paper ITSGM (Interpolation On a Tangent Space of the Grassmann Manifold), allows through the passage to the tangent space of the Grassmann manifold, to approximate accurately the reduced order basis associated to a new untrained parameter. This basis is used afterwards to build the interpolated ROM describing the temporal dynamics by performing the Galerkin projection on the high fidelity model. Such Galerkin ROMs require to access to the underlying high fidelity model, leading by that to intrusive ROMs. In this paper, and contrary to the ITSGM/Galerkin approach, we propose a non-intrusive reduced order modeling method which is independent of the governing equations. This method is named through this paper Bi-CITSGM (Bi-Calibrated ITSGM). It consists first to interpolate the spatial and temporal POD sampling bases considered as representatives of points on Grassmann manifolds, by the ITSGM method. Then, the resulting bases modes are reclassified by introducing two orthogonal matrices. These calibration matrices are determined as analytical solutions of two optimization problems. Results on the flow problem past a circular cylinder where the parameter of interpolation is the Reynolds number, show that for new untrained Reynolds number values, the developed approach produces satisfyingly accurate solutions in a real computational time.

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Section: Description Of the Methodsmentioning

confidence: 99%

“…Parametrized physical problems arise in many practical engineering design and analysis problems such as aerospace engineering [2,3], biomedical engineering [4], flow control [5] etc. The numerical computational cost of these applications can be exorbitant.…”

Section: Introductionmentioning

confidence: 99%

Non intrusive method for parametric model order reduction using a bi-calibrated interpolation on the Grassmann manifold

Oulghelou

Allery

2019

Preprint

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“…FIGURE 1: Computation grid of the high-lift LS configuration of the A320 in the take-off position Choosing two different optimizations using only geometrical parameters (geometrical optimization) or the angle of attack and the Mach number (total optimization), they have found for both optimizations quite similar optimal geometric positions : a flap rotation to increase the lift and an upward slat rotation to reduce the drag. In another aerodynamic multi-objective optimization, the study of Lu et al (2017), proposed a flexible variable camber trailing edge of the flap for a two-element airfoil-flap able to camber its shape smoothly at the take-off and landing conditions. They have found that a variable camber of the flap of 50 % of its chord can increase the lift coefficient by about 8 % and the lift-to-drag ratio by 7 % for the take-off configuration and improve the lift coefficient at a stall angle of attack by 1.3 %.…”

Section: Cmentioning

confidence: 99%

Numerical investigation of frequency-amplitude effects of dynamic morphing for a high-lift configuration at high Reynolds number

Marouf

Tekap

Simiriotis

et al. 2020

HFF

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Purpose The purpose of this study illustrates the morphing effects around a large-scale high-lift configuration of the Airbus A320 with two elements airfoil-flap in the take-off position. The flow around the airfoil-flap and the near wake are analysed in the static case and under time-dependent vibration of the flap trailing-edge known as the dynamic morphing. Design/methodology/approach Experimental results obtained in the subsonic wind tunnel S1 of Institut de Mécanique des Fluides de Toulouse of a single wing are discussed with high-fidelity numerical results obtained by using the Navier–Stokes multi-block (NSMB) code with advanced turbulent modelling able to capture the predominant instabilities and coherent structure dynamics. An explanation of the dynamic time-dependent grid deformation is provided, which is used in the NSMB code to simulate the flap’s trailing-edge deformation in the morphing configuration. Finally, power spectral density is performed to reveal the coherent wake structures and their modification because of the morphing. Findings Frequency of vibration and amplitude of deformation effects are investigated for different morphing cases. Optimal morphing regions at a specific frequency and a slight deformation were able to attenuate the predominant natural shear-layer frequency and to considerably decrease the width of the von Kármán vortices with a simultaneous increase of aerodynamic performances. Originality/value The new concept of future morphed wings is proposed for a large scale A320 prototype at the take-off position. The dynamic morphing of the flap’s trailing-edge is simulated for the first time for high-lift two-element configuration. In addition, the wake analysis performed helped to show the turbulent structures according to the organised eddy simulation model.

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“…We compared for this present study the flow in 2D in the Fig. 2 (right) the numerical simulation to the results of GA(w)-2 airfoil-flap (W. LU [9]) which is almost similar airfoil properties as the A320, but with a smaller flap. The simulations have been carried out with the NSMB solver.…”

Section: B Numerical Parametersmentioning

confidence: 99%

Evaluation of the aerodynamic performance increase thanks to a morphing A320 wing with high-lift flap by means of CFD Hi-Fi approaches

Marouf

Hoarau

Vos

et al. 2019

AIAA Aviation 2019 Forum

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The flow around a two-element large scale wing-flap configuration with a dynamic morphing of the flap's trailing-edge is investigated by means of two dimensional and three-dimensional high-fidelity numerical simulation. A detailed explanation is provided for the implemented methods to compute the time depend displacement and the dynamic grid deformation in the NSMB code. The aim of this study is to simulate the morphing of the flap's trailing-edge at high frequency and low amplitude actuations. The morphing introduces new small anticlockwise vortices in the wake at high frequency. This effects are also observed in TR-PIV experimental results. This technique creates an eddy blocking effect in the wake shear-layer, which leads to a breakdown of the coherent structures in the wake, make a thinner wake and decrease the aerodynamic noise. Several unsteady simulations were carried to find out the optimal frequencies and amplitudes allowing an increase of the aerodynamic performances as the lift force and decrease the drag.

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Aerodynamic optimization and mechanism design of flexible variable camber trailing-edge flap

Cited by 46 publications

References 6 publications

Non intrusive method for parametric model order reduction using a bi-calibrated interpolation on the Grassmann manifold

Non intrusive method for parametric model order reduction using a bi-calibrated interpolation on the Grassmann manifold

Numerical investigation of frequency-amplitude effects of dynamic morphing for a high-lift configuration at high Reynolds number

Evaluation of the aerodynamic performance increase thanks to a morphing A320 wing with high-lift flap by means of CFD Hi-Fi approaches

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