Recent Developments on Fluid Structure Interaction Using the Navier Stokes Multi Block (NSMB) CFD Solver

This study investigates the physical mechanisms of the use of Active Flow Control (AFC) associated with morphing through cambering approach in a high-lift wing-flap system. Results of high-fidelity numerical simulations are examined at high Reynolds number (Re/c) of 4.6 Million. Adapted turbulence models are used to capture the flow separation and the development of coherent structures. Different approaches of AFC are proposed to suppress the flow separation located approximately at 60% of the cambered flap's chord. The present study focuses on AFC using steady continuous jet, unsteady valves or oscillators (pulsed blowing) and more precisely the Zero Net Mass Flux (synthetic jet) with the blowing-suction approach. The AFC at an optimal velocity and frequency of actuation enabled an enforcement of the flow re-attachment and a delay of the flow separation. The minimum jet velocity and a feasible vibration frequency are discussed providing a practically complete control of the separation regarding the high deflection angle and cambering dimensions. As a main result of the study, the pressure distribution is enhanced over both wing-flap surfaces, adverse pressure gradients are suppressed and the re-attachment of the boundary layer is obtained. These results have the potential to increase significantly the aerodynamic efficiency of aircraft during the take-off and landing phases.

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“…A variety of papers have been published on NSMB, examples are in Refs. [9][10][11][12][13][14][15][16][17][18][19].…”

Section: Nsmb Cfd Solver and Numerical Methodsmentioning

confidence: 99%

Unsteady CFD simulations for Active Flow Control

Marouf

Chouippe

Vos

et al. 2021

Aiaa Aviation 2021 Forum

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“…The CFD simulations were carried out using the Navier Stokes Multi Block solver NSMB developed in a consortium composed of different universities and industries [18,19]. NSMB is a cell-centered finite volume solver using multi block structured grids.…”

Section: Computational Setup a Nsmb Solver Descriptionmentioning

confidence: 99%

CFD simulations of active flow control devices applied on a cambered flap

Marouf

Truong

Hoarau

et al. 2022

AIAA SCITECH 2022 Forum

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“…Over the last years, the modeling of control surface deflections with CFD solvers has been subject to several projects, such as ComFlite [6], Digital-X [7], VicToria and Mephisto [8], as well as several publications, for instance by Vos et al [9], Sørensen et al [10] and Clifton et al [11]. Similarly, aeroelastic simulations of aircraft using coupled iterative CFD-CSM simulations with high-fidelity CFD methods (RANS or higher precision) and detailed structural models have been investigated by several authors such as Voß et al [12], Fornasier et al [13] and Stickan et al [14].…”

Section: Introductionmentioning

confidence: 99%

“…Due to the compatibility of the Chimera implementation with hybrid grids as well as intersecting surfaces, it offers the possibility to handle complex geometries as well as different types of control surfaces. Hence, the presented solution is considered to be advantageous compared to methods which are using sliding mesh approaches as described in [5], since the Chimera technique is more robust combined with mesh deformation, or to solutions which are limited to structured grids only, as presented in [9], where the mesh generation process can be time-consuming and difficult for complex geometries.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic simulations of a delta wing with a Chimera approach for deflected control surfaces

2021

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A numerical tool for the computation of aircraft control surface aerodynamics with flexibility effects is presented. The solution is based on coupled Computational Fluid Dynamics (CFD) and Computational Structural Mechanics (CSM) simulations embedded in the multidisciplinary simulation environment SimServer. In SimServer, the DLR-TAU Code is utilized to obtain the CFD solution by solving the Reynolds-Averaged Navier–Stokes (RANS) equations. Structural displacements are computed with a modal solver. The Chimera implementation of SimServer, suited for hybrid grids, is applied to model the control surfaces. Numerical simulations with the flexible Chimera method are performed for the Model53 wing configuration, which is a generic delta wing with a deployed slat as well as an inboard and outboard trailing edge flap. Aerodynamic and aeroelastic simulations at high dynamic pressure $$q=45$$ q = 45 kPa and transonic speed $${\text {Ma}} = 0.8$$ Ma = 0.8 are performed for several angles of attack $$10^\circ \le \alpha \le 25^\circ$$ 10 ∘ ≤ α ≤ 25 ∘ and flap deflection angles $$-30^\circ \le \delta \le 30^\circ$$ - 30 ∘ ≤ δ ≤ 30 ∘ . The effect of structural deformations on the flow field and control surface effectiveness are analyzed and compared to computations of components treated fully rigid. At the targeted freestream condition $$M=0.8$$ M = 0.8 and $${\text {Re}}=15.1 \times 10^7$$ Re = 15.1 × 10 7 , the flow field around the Model53 configuration is characterized by the interaction of vortices and shock waves. The results of the lift and pitching moment coefficient for the rigid and flexible configuration revealed the importance of taking the structural flexibility into account in order to obtain more accurate results for the considered range of flap deflections. Furthermore, the computational effort of the aerodynamic and aeroelastic simulations are evaluated. The increase in computational effort is shown to be adequate for the given increase in accuracy.

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Recent Developments on Fluid Structure Interaction Using the Navier Stokes Multi Block (NSMB) CFD Solver

Cited by 7 publications

References 9 publications

Unsteady CFD simulations for Active Flow Control

Unsteady CFD simulations for Active Flow Control

CFD simulations of active flow control devices applied on a cambered flap

Aeroelastic simulations of a delta wing with a Chimera approach for deflected control surfaces

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