Computational Modeling of Variable Droop Leading Edge in Forward Flight

Bain, Jeremy; Sankar, Lakshmi N.; Prasad, J. V. R.; Bauchau, Oliver A.; Peters, David A.; He, Chengjian

doi:10.2514/6.2008-3872

Cited by 7 publications

(4 citation statements)

References 6 publications

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“…The motion equations of both models are AoA = 10 + 10sin( ωt ). Considering the limitations of the S‐A turbulence model for dynamic stall cases and the correction of the wing tunnel wall surface, it can be concluded that the flow characteristics are consistent with the experimental results 54 and the reference computed values 55 . The results show that the proposed overset assembly method is suitable for the unsteady simulation of a dynamic model.…”

Section: Integration and Verification Of The Chimera Cfd Solversupporting

confidence: 57%

A robust overset assembly method for multiple overlapping bodies

Shi

2020

Numerical Methods in Fluids

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Summary A robust overset assembly method allowing for multiple overlapping bodies is presented. This method extends the overset assembly method to deal with the interference between objects and prevents the failure of the search for donor cells due to the complex shape of the models. The donor cells are searched before identifying the boundary of the chimera interpolation. By selecting interpolation cells only in areas with donor cells, the final overset interpolation boundary cells can always find their donor cells, which prevents orphan points and achieves excellent robustness. First, the implementation of the proposed assembly method is described in detail. Subsequently, the usability and efficiency of the method are verified using several cases. Finally, the integration strategy of the computational fluid dynamics solver based on overset interpolation with the modification of the boundary type is described and verified using practical cases with overlapping bodies. The results demonstrate the applicability of the proposed overset grid assembly method.

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Section: Integration and Verification Of The Chimera Cfd Solversupporting

confidence: 57%

A robust overset assembly method for multiple overlapping bodies

Shi

2020

Numerical Methods in Fluids

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“…Concepts that have been studied for reducing slat noise include brushes 1,7 , an extended blade seal 8 , serrated trailing edges, slat-cove fillers (SCFs) 7,[9][10][11][12][13] and drooped leading edges (DLEs) [14][15][16][17][18][19] . Brushes applied at the slat cusp and trailing edge, intended to damp the fluctuating pressures there, increase drag at cruise and provide only a modest noise benefit.…”

Section: Introductionmentioning

confidence: 99%

Development of a SMA-Based, Slat-Gap Filler for Airframe Noise Reduction

Turner

Long

2015

23rd AIAA/AHS Adaptive Structures Conference

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Noise produced by unsteady flow around aircraft structures, termed airframe noise, is an important source of aircraft noise during the approach and landing phases of flight. Conventional leading-edge-slat devices for high lift on typical transport aircraft are a prominent source of airframe noise. Many concepts for slat noise reduction have been investigated. Slat-cove fillers have emerged as an attractive solution, but they maintain the gap flow, leaving some noise production mechanisms unabated, and thus represent a nonoptimal solution. Drooped-leading-edge (DLE) concepts have been proposed as "optimal" because the gap flow is eliminated. The deployed leading edge device is not distinct and separate from the main wing in DLE concepts and the high-lift performance suffers at high angles of attack () as a consequence. Elusive high- performance and excessive weight penalty have stymied DLE development. The fact that high-lift performance of DLE systems is only affected at high  suggests another concept that simultaneously achieves the high-lift of the baseline airfoil and the noise reduction of DLE concepts. The concept involves utilizing a conventional leading-edge slat device and a deformable structure that is deployed from the leading edge of the main wing and closes the gap between the slat and main wing, termed a slat-gap filler (SGF). The deployable structure consists of a portion of the skin of the main wing and it is driven in conjunction with the slat during deployment and retraction. Benchtop models have been developed to assess the feasibility and to study important parameters. Computational models have assisted in the bench-top model design and provided valuable insight in the parameter space as well as the feasibility. NomenclatureA = planform area CL = lift coefficient Cp = pressure coefficient Cusp = lower trailing edge of slat DLE = drooped leading edge L = aerodynamic lift OML = outer mold line RoFC = region of fixed curvature SCF = slat-cove filler SGF = slat-gap filler SMA = shape memory alloy  = angle of attack  = mass density  Af ,  As = austenite finish/start critical stress 1 Research Engineer, Structural Acoustics Branch, 2 N Dryden Street/Mail Stop 463, AIAA Senior Member 2 Designer III, TEAMS2 -Structural Dynamics Branch, 4B W Taylor Street/Mail Stop 230 Downloaded by PURDUE UNIVERSITY on July 31, 2015 | http://arc.aiaa.org |

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“…It is desirable, from an aeroacoustic noise perspective, to eliminate the flow between the slat and main wing to minimize the noise production mechanisms and maximize the noise benefit. A class of structural concepts of this type, known as drooped leading edge (DLE) concepts, are represented by the schematic in Figure 2 and have been proposed and studied by various research groups specifically to investigate the possibility of eliminating the slat-gap flow [17][18][19][20][21][22] .…”

Section: Slat Noise Reduction Conceptsmentioning

confidence: 99%

Computational Modeling of a Mechanized Bench-Top Apparatus for Leading-Edge Slat Noise Treatment Device Prototypes

Turner

Moore

Long

2017

25th AIAA/AHS Adaptive Structures Conference

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Airframe noise is a growing concern in the vicinity of airports because of population growth and gains in engine noise reduction that have rendered the airframe an equal contributor during the approach and landing phases of flight for many transport aircraft. The leading-edge-slat device of a typical high-lift system for transport aircraft is a prominent source of airframe noise. Two technologies have significant potential for slat noise reduction; the slat-cove filler (SCF) and the slat-gap filler (SGF). Previous work was done on a 2D section of a transport-aircraft wing to demonstrate the implementation feasibility of these concepts. Benchtop hardware was developed in that work for qualitative parametric study. The benchtop models were mechanized for quantitative measurements of performance. Computational models of the mechanized benchtop apparatus for the SCF were developed and the performance of the system for five different SCF assemblies is demonstrated.

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Computational Modeling of Variable Droop Leading Edge in Forward Flight

Cited by 7 publications

References 6 publications

A robust overset assembly method for multiple overlapping bodies

A robust overset assembly method for multiple overlapping bodies

Development of a SMA-Based, Slat-Gap Filler for Airframe Noise Reduction

Computational Modeling of a Mechanized Bench-Top Apparatus for Leading-Edge Slat Noise Treatment Device Prototypes

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