Aeroelastic Modeling and Drag Optimization of Flexible Wing Aircraft with Variable Camber Continuous Trailing Edge Flap

Lebofsky, Sonia; Ting, Eric B.; Nguyen, Nhan T.; Trinh, Khanh

doi:10.2514/6.2014-2443

Cited by 25 publications

(19 citation statements)

References 10 publications

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“…Agreement between VORVIEW/VORLAX, Cart3D, and wind tunnel results have been shown for the GTM platform. 1,2,20 In general, both VORVIEW and Cart3D seem to have similar predictive capabilities when compressibility is not a factor. Figure 10 shows a panel/polygon discretization of the UWAL wind tunnel model geometry within VORVIEW.…”

Section: Vortex-lattice Aerodynamic Modelmentioning

confidence: 71%

“…A coupled aero-structural static aeroelastic model is used that draws from the coupled vortex-lattice finite-element framework used in previous studies. [18][19][20] Figure 15 represents the high level coupling conducted by the iterations in the aeroelastic code. The static aeroelastic code is used to map an input flight condition into the respective static aeroelastic deformed wing shape and corresponding aerodynamic qualities.…”

Section: Static Aeroelasticity Modelmentioning

confidence: 99%

“…Data corresponding to wind tunnel runs where the VCCTEF is set at zero deflection, or FLAP0, corresponds to runs 18,19,20,21,22,23,24, 69, 70, 71, and 72. Table 3 represents VCCTEF flap deflection data for each of the sections/segments.…”

Section: A Flap0mentioning

confidence: 99%

“…The aeroelastic analysis uses an FEM approach similar to past investigations, [15][16][17] and the resulting coupled finite-element vortex-lattice static aeroelastic framework has also been applied in past studies. [18][19][20] The coupled finite-element vortex-lattice static aeroelastic model of the UWAL wind tunnel model is able to estimate aeroelastic deformations and generate flexible model lift curves that are compared to UWAL experimental test results. The automated geometry generation tool is also able to model VCCTEF deflections on the UWAL model, and thus multiple experimental test result cases are examined.…”

Section: Introductionmentioning

confidence: 99%

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Static Aeroelastic Modeling of a Sub-Scale Wind Tunnel Model with Novel Flap Concept

Ting

Nguyen

Lebofsky

2015

56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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This paper examines the static aeroelastic modeling of a flexible wind tunnel model equipped with a novel control effector known as the Variable Camber Continuous Trailing Edge Flap (VCCTEF) system. The wind tunnel model is an approximately 10% sub-scale version of a wing designed to be equipped on a commercial transport aircraft such as the full-scale NASA Generic Transport Model (GTM). The structure of the model is made highly flexible such that a 10% of semi-span wing tip deflection is expected at a design lift condition, and a representation of the VCCTEF concept is incorporated on the model. Static aeroelastic modeling is conducted by using a representative single beam structural finite-element model coupled to a vortex-lattice aerodynamic model. The resulting aeroelastic model of the flexible wind tunnel model is compared against experimental wind tunnel test results from the actual model tested at the University of Washington Aeronautical Laboratory (UWAL). Comparison cases are made using reference and VICON measurements of VCCTEF flap deflections from the wind tunnel test data, and percent errors between the lift curve parameters are presented. The results show up to a maximum percent of error of <10% with regards to lift curve slope values between the aeroelastic model and the UWAL test data. The agreement of lift curve slope values from the aeroelastic model and experimental test results serves as validation for the coupled vortex-lattice finite-element static aeroelastic model.

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Section: Vortex-lattice Aerodynamic Modelmentioning

confidence: 71%

Section: Static Aeroelasticity Modelmentioning

confidence: 99%

Section: A Flap0mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Static Aeroelastic Modeling of a Sub-Scale Wind Tunnel Model with Novel Flap Concept

Ting

Nguyen

Lebofsky

2015

56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…Several previous conceptual design studies have been conducted investigating the potential of the VCCTEF system for drag reduction at off-design cruise flight conditions for a flexible wing aircraft representative of a current generation commercial aircraft model. [5][6][7] These studies produced results showing that a VCCTEF system does have potential for effectively reshaping the aircraft wing during flight for significant drag reduction benefits. Experimental wind tunnel studies were also conducted to show the benefit and potential of a VCCTEF system on a flexible wing.…”

Section: Introductionmentioning

confidence: 99%

Optimization for Load Alleviation of Truss-Braced Wing Aircraft With Variable Camber Continuous Trailing Edge Flap

Lebofsky

Ting

Trinh

et al. 2015

33rd AIAA Applied Aerodynamics Conference

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This paper focuses on load alleviation optimization for a high aspect ratio truss braced wing (TBW) aircraft. The TBW aircraft model is based on the Subsonic Ultra Green Aircraft Research (SUGAR) concept developed by Boeing, with the wing structures of the model modified to include a novel aerodynamic control surface known as the Variable Camber Continuous Trailing Edge Flap (VCCTEF). The purpose of the study is to investigate the effectiveness of a Performance Adaptive Aeroelastic Wing (PAAW) technology, specifically the VCCTEF, for alleviating load on the TBW wing during flight maneuver. The specific flight maneuver under consideration in this study is a 2.5g pull-up maneuver. Constrained gradient-based optimization is conducted to tailor the deflections of the VC-CTEF such that bending moment along the wing is minimized at the 2.5g pull-up flight condition. Aerodynamic modeling for this study is conducted using a vortex-lattice method code called Vorlax. A non-linear finite element analysis (FEA) method is constructed for analyzing the structural deformation and resulting bending moment along the wing of the aircraft with the inclusion of effects from tension-stiffening due to axial loading in the truss. This study is the first phase of several, and involves optimization of a rigid wing aircraft for preliminary analysis. Future studies will incoporate flexible wing structures with aeroelastic interactions and deformations. The results of this first phase positively demonstrate the potential of utilizing the novel control surface on modern aircraft wing designs for shaping control in order to provide load alleviation during flight maneuver.

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Numerical study of a supercritical airfoil/wing with variable-camber technology

Wei

Zhang

Chen

et al. 2020

Chinese Journal of Aeronautics

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Aeroelastic Modeling and Drag Optimization of Flexible Wing Aircraft with Variable Camber Continuous Trailing Edge Flap

Cited by 25 publications

References 10 publications

Static Aeroelastic Modeling of a Sub-Scale Wind Tunnel Model with Novel Flap Concept

Static Aeroelastic Modeling of a Sub-Scale Wind Tunnel Model with Novel Flap Concept

Optimization for Load Alleviation of Truss-Braced Wing Aircraft With Variable Camber Continuous Trailing Edge Flap

Numerical study of a supercritical airfoil/wing with variable-camber technology

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