Two-dimensional aircraft high lift system design and optimization

Besnard, Eric; Schmitz, Adeline; Boscher, Erwan; Garcia, Nicolas M.; Cebecit, Tuncer

doi:10.2514/6.1998-123

Cited by 24 publications

(10 citation statements)

References 9 publications

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“…One area of signi cant interest is the design and optimization of high-lift systems deployed during takeoff and landing. 6 For such design cases, surface geometry modi cations are generally limited to small regions, such as the leading-edge region of a ap element. Thus, a design method must work well in leading-edge regions before it can be applied to such challenging design tasks.…”

Section: William E Milholen II ¤ Nasa Langley Research Center Hamptmentioning

confidence: 99%

Efficient Inverse Aerodynamic Design Method for Subsonic Flows

Milholen

2001

Journal of Aircraft

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Computational Fluid Dynamics based design methods are maturing to the point that they are beginning to be used in the aircraft design process. Many design methods however have demonstrated de ciencies in the leading edge region of airfoil sections. The objective of the present research is to develop an e cient inverse design method which i s v alid in the leading edge region. The new design method is a streamline curvature method, and a new technique is presented for modeling the variation of the streamline curvature normal to the surface. The new design method allows the surface coordinates to move normal to the surface, and has been incorporated into the Constrained Direct Iterative Surface Curvature CDISC design method. The accuracy and e ciency of the design method is demonstrated using both two-dimensional and three-dimensional design cases.

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Section: William E Milholen II ¤ Nasa Langley Research Center Hamptmentioning

confidence: 99%

Efficient Inverse Aerodynamic Design Method for Subsonic Flows

Milholen

2001

Journal of Aircraft

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“…Besnard et al performed optimizations of high-lift systems using an interactive boundary layer approach. 29 All of these earlier works on multi-element airfoil design obtained the necessary gradients by finite difference methods. More recently, discrete adjoint gradients have also been used for the design of multi-element airfoil configurations.…”

Section: Introductionmentioning

confidence: 99%

Multi-Element High-Lift Configuration Design Optimization Using Viscous Continuous Adjoint Method

Kim

Alonso

Jameson

2004

Journal of Aircraft

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An adjoint-based Navier-Stokes design and optimization method for two-dimensional multi-element high-lift configurations is derived and presented. The compressible Reynolds-averaged Navier-Stokes equations are used as a flow model together with the Spalart-Allmaras turbulence model to account for high Reynolds number effects. When a viscous continuous adjoint formulation is used, the necessary aerodynamic gradient information is obtained with large computational savings over traditional finite difference methods. The high-lift configuration parallel design method uses a point-to-point matched multiblock grid system and the message passing interface standard for communication in both the flow and adjoint calculations. Airfoil shape, element positioning, and angle of attack are used as design variables. The prediction of high-lift flows around a baseline three-element airfoil configuration, denoted as 30P30N, is validated by comparison with available experimental data. Finally, several design results that verify the potential of the method for high-lift system design and optimization are presented. The design examples include a multi-element inverse design problem and the following optimization problems: lift coefficient maximization, lift-to-drag ratio maximization, and the maximum lift coefficient maximization problem for both the RAE2822 single-element airfoil and the 30P30N multi-element airfoil. NomenclatureC d , C l = airfoil coefficients of drag and lift C lmax = maximum lift coefficientboundary shape G G = gradient vector H = total enthalpy I = cost function L = lift M ∞ = freestream Mach number p = static pressure p d = desired target static pressure R = governing equations or residual Re = Reynolds number S = surface area t/c = thickness-to-chord ratio w = conservative flow variables in Cartesian coordinates x,y = Cartesian coordinates y + = dimensionless wall distance α = angle of attack α cl max = stall angle of attack δ = first variation λ = step size in steepest descent method ψ = Lagrange multiplier, costate or adjoint variables

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“…In particular, the application of numerical optimization algorithms combined with Computational Fluid Dynamics (CFD) methods is becoming one of the most active areas of research. In this context, Reynolds Averaged Navier-Stokes (RANS) methods have been extensively used for the optimization of 2D high-lift airfoil [2][3][4][5][6][7][8] and, recently, for full 3D configurations 9,10 . However, the high turn around time of RANS simulations make them unsuitable to perform optimization of 3D high lift geometry at the preliminary design stages, which is the focus of this work.…”

Section: Introductionmentioning

confidence: 99%

A Rapid Approach to the Aerodynamic Design of a Flexible High-Lift Wing

Trapani

Savill

Kipouros

et al. 2014

32nd AIAA Applied Aerodynamics Conference

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The development and application of a rapid methodology for the optimization of HighLift configurations is here presented. The proposed framework includes a quasi-threedimensional method to simulate the aerodynamic performance, a rapid method for the estimation of the static aero-elastic effects, and two multi-objective optimization algorithms: the well-know NSGA-II and the innovative multi-objective Tabu Search. After an extensive validation study of both the aerodynamic simulation and the aero-structure coupling method, the framework is used to optimize the landing performance of the KH3Y configuration. The deployment settings of the full-span slat and of the two single-slotted flap elements, inboard and outboard, are identified as design variables. The maximum lift coefficient and the lift over drag ratio at the approach angle of attack are used as objective functions. Two optimization setups are executed to assess the influence of the wing flexibility on the revealed Pareto Front. In both cases the selected optimization algorithm has been able to improve the performance of the datum. Moreover, the results show the importance of considering aero-structure influences early on in the design process. Finally, parallel coordinate visualization techniques are used to analyze the peculiar Search Pattern revealed. NomenclatureK Stiffness matrix S Flexibility matrix u Displacements array Z Forces and moments array cd Drag coefficient cl Lift coefficient cl appr Lift coefficient at approach angle of attack L/D appr Lift to Drag ratio at approach angle of attack M Number of wing sections spanwise * EngD Researcher, School of Engineering, Centre for Propulsion. Student Member. g.trapani@cranfield.ac.uk

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Two-dimensional aircraft high lift system design and optimization

Cited by 24 publications

References 9 publications

Efficient Inverse Aerodynamic Design Method for Subsonic Flows

Efficient Inverse Aerodynamic Design Method for Subsonic Flows

Multi-Element High-Lift Configuration Design Optimization Using Viscous Continuous Adjoint Method

A Rapid Approach to the Aerodynamic Design of a Flexible High-Lift Wing

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