Modeling and Simulation of Morphing Wing Aircraft

Obradovic, Borna; Subbarao, Kamesh

doi:10.1002/9781119964032.ch5

Cited by 6 publications

(5 citation statements)

References 14 publications

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“…On the numerical side, more work has been undertaken to quantify the efficiency of morphing concepts. Starting with optimization problems using low-fidelity panel-based methods as used by Molinari et al [13] or the Vortex-Lattice Methods (VLM) as used by Obradovic et al [14], the Reynolds-Averaged Navier-Stokes (RANS) solver coupled with various turbulence models has also been applied for morphing wings applications, such as in Lyu et al [15] where the Spalart-Allmaras model was used, up to 5% drag reduction was reported. Ai et al [16] studied an airfoil fitted with a morphing TEF, and found that the morphing TEF is more aerodynamically efficient at the angles of attack studied.…”

Section: Aoamentioning

confidence: 99%

Analysis of a 3D Unsteady Morphing Wing with Seamless Side-edge Transition

Abdessemed

Yao

Bouferrouk

et al. 2018

2018 Applied Aerodynamics Conference

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Section: Aoamentioning

confidence: 99%

Analysis of a 3D Unsteady Morphing Wing with Seamless Side-edge Transition

Abdessemed

Yao

Bouferrouk

et al. 2018

2018 Applied Aerodynamics Conference

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“…On the numerical side, comparatively more work has been undertaken to quantify the aerodynamic efficiency of morphing concepts. Starting with optimisation problems using low-fidelity panel-based methods by Molinari et al [27] or the Vortex-Lattice Methods (VLM) by Obradovic et al [28] and Koreanschi et al [29], the Reynolds-Averaged Navier-Stokes (RANS) solver, coupled with various turbulence models, has also been applied for morphing wings applications, e.g., Lyu et al [30] have used the Spalart-Allmaras turbulence model with up to 5% drag reduction achieved. Finally, Jawahar et al [31] used a hybrid RANS-LES approach, so-called Detached Eddy Simulation (DES), to study the aerodynamic and aeroacoustic flow around an airfoil with a rigid and morphing TEF.…”

Section: Introductionmentioning

confidence: 99%

Effects of an Unsteady Morphing Wing with Seamless Side-Edge Transition on Aerodynamic Performance

2022

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This paper presents an unsteady flow analysis of a 3D wing with a morphing trailing edge flap (TEF) and a seamless side-edge transition between the morphed and static parts of a wing by introducing an unsteady parametrization method. First, a 3D steady Reynolds-averaged Navier–Stokes (RANS) analysis of a statically morphed TEF with seamless transition is performed and the results are compared with both a baseline clean wing and a wing with a traditional hinged flap configuration at a Reynolds number of 0.7 × 106 for a range of angles of attack (AoA), from 4° to 15°. This study extends some previous published work by examining the inherent unsteady 3D effects due to the presence of the seamless transition. It is found that in the pre-stall regime, the statically morphed wing produces a maximum of a 22% higher lift and a near constant drag reduction of 25% compared with the hinged flap wing, resulting in up to 40% enhancement in the aerodynamic efficiency (i.e., lift/drag ratio). Second, unsteady flow analysis of the dynamically morphing TEF with seamless flap side-edge transition is performed to provide further insights into the dynamic lift and drag forces during the flap motions at three pre-defined morphing frequencies of 4 Hz, 6 Hz, and 8 Hz, respectively. Results have shown that an initially large overshoot in the drag coefficient is observed due to unsteady flow effects induced by the dynamically morphing wing; the overshoot is proportional to the morphing frequency which indicates the need to account for dynamic morphing effects in the design phase of a morphing wing.

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“…For example, the use of steady and unsteady vortex-lattice methods (VLMs) was popular for morphing configurations, as they offered better accuracy than analytical methods or strip line theory, while still consuming less CPU time than the full Navier–Stokes simulations. For instance, VLM was used to model a morphing Gull wing (Obradovic and Subbarao, 2012) to predict and optimise the lift-to-drag ratio of a variable camber morphing wing (Urnes and Nguyen, 2013), and to compare the performance of various morphing wing concepts that have optimised camber and span (Molinari et al , 2011). Later, a double-lattice method corrected by high accuracy CFD data was developed and used to model a morphing wing tip concept (Chekkal et al , 2014).…”

Section: Introductionmentioning

confidence: 99%

Morphing airfoils analysis using dynamic meshing

Abdessemed

Yao

Bouferrouk

et al. 2018

HFF

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Purpose -The purpose of this paper is to use dynamic meshing to perform CFD analyses of a NACA 0012 airfoil fitted with a morphing trailing-edge (TE) flap when it undergoes static and time dependent morphing. The steady CFD predictions of the original and morphing airfoils are validated against published data. The study also investigates an airfoil with a hinged trailing edge flap for aerodynamic performance comparison. The study further extends to an unsteady CFD analysis of a dynamically morphing trailing edge flap for proof-of-concept and also to realise its potential for future applications.Design/methodology/approach -An existing parametrization method was modified and implemented in a user-defined function (UDF) to perform dynamic meshing which is essential for morphing airfoil unsteady simulations. The results from the deformed mesh were verified to ensure the validity of the adopted mesh deformation method. ANSYS Fluent software was used to perform steady and unsteady analysis and the results were compared with computational predictions.Findings -Steady computational results are in good agreement with those from OpenFOAM for a non-morphing airfoil, and for a morphed airfoil with a maximum TE deflection equal to 5% of the chord. The results obtained by ANSYS Fluent show that an average of 6.5% increase in lift-to-drag ratio is achieved, compared with a hinged flap airfoil with the same TE deflection. By using dynamic meshing, unsteady transient simulations reveal that the local flow field is influenced by the morphing motion.Originality/value -An airfoil parametrization method was modified to introduce time dependent morphing and used to drive dynamic meshing through an in-house developed UDF. The morphed airfoil's superior aerodynamic performance was demonstrated in comparison with traditional hinged trailing edge flap. A methodology was developed to perform unsteady transient analysis of a morphing airfoil at high angles of attack beyond stall, and to compare with published data. Unsteady predictions have shown signs of rich flow features, paving the way for further research into the effects of a dynamic flap on the flow physics.

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Modeling and Simulation of Morphing Wing Aircraft

Cited by 6 publications

References 14 publications

Analysis of a 3D Unsteady Morphing Wing with Seamless Side-edge Transition

Analysis of a 3D Unsteady Morphing Wing with Seamless Side-edge Transition

Effects of an Unsteady Morphing Wing with Seamless Side-Edge Transition on Aerodynamic Performance

Morphing airfoils analysis using dynamic meshing

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