Simultaneous Excitation of Multiple-Input/Multiple-Output CFD-Based Unsteady Aerodynamic Systems

Silva, Walter A.

doi:10.2514/1.34328

Cited by 72 publications

(14 citation statements)

References 22 publications

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“…(1) Generate the number of functions from a selected family of orthogonal functions (Silva 2008) that corresponds to the number of structural modes.…”

Section: Fun3d Reduced-order Modelsmentioning

confidence: 99%

“…Email: Walter.A.Silva@nasa.gov rapidly generate V-g-f plots and/or root locus plots were not available. However, with the development of reducedorder modelling (ROM) methods (Silva 2008;Biedron 2009, 2010), the rapid generation of root locus plots using CFD-based unsteady aerodynamics is now available to aeroelasticians.…”

Section: Introductionmentioning

confidence: 99%

“…Kim's method consists of using simultaneous staggered step inputs, one per mode, and then recovering the individual responses from this simultaneous excitation. Silva (2008) has developed a method that enables the simultaneous excitation of the structural modes using orthogonal functions. Both of these methods require only a single CFD solution and the methods are independent of the number of structural modes.…”

Section: Introductionmentioning

confidence: 99%

“…Silva (2007) has also developed a method for generating static aeroelastic solutions and matched-point aeroelastic solutions using a ROM. The methods developed by Silva (2008Silva ( , 2007 have already been implemented in the FUN3D CFD code. In addition, methods for generating root locus plots of the combined structural state-space model and unsteady aerodynamic state-space model were developed by Silva, Vatsa, and Biedron (2009).…”

Section: Introductionmentioning

confidence: 99%

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Evaluation of linear, inviscid, viscous, and reduced-order modelling aeroelastic solutions of the AGARD 445.6 wing using root locus analysis

Silva

Chwalowski

Perry

2014

International Journal of Computational Fluid Dynamics

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Reduced-order modelling (ROM) methods are applied to the Computational Fluid Dynamics (CFD)-based aeroelastic analysis of the AGARD 445.6 wing in order to gain insight regarding well-known discrepancies between the aeroelastic analyses and the experimental results. The results presented include aeroelastic solutions using the inviscid Computational Aeroelasticity Programme-Transonic Small Disturbance (CAP-TSD) code and the FUN3D code (Euler and Navier-Stokes). Full CFD aeroelastic solutions and ROM aeroelastic solutions, computed at several Mach numbers, are presented in the form of root locus plots in order to better reveal the aeroelastic root migrations with increasing dynamic pressure. Important conclusions are drawn from these results including the ability of the linear CAP-TSD code to accurately predict the entire experimental flutter boundary (repeat of analyses performed in the 1980s), that the Euler solutions at supersonic conditions indicate that the third mode is always unstable, and that the FUN3D Navier-Stokes solutions stabilize the unstable third mode seen in the Euler solutions. IntroductionClassical linear aeroelastic analyses typically produce velocity-damping-frequency (V-g-f) plots and/or root locus plots. The use of these plots has enabled the aeroelastician to view the nature of the flutter mechanism(s) in addition to identifying the condition(s) at which flutter occurs. The rapid creation of these plots was facilitated by the use of linear unsteady aerodynamics and linear aeroelastic equations of motion (Adams and Hoadley 1993).During the last few years, higher order CFD-based methods have become an important method for the computation of nonlinear unsteady aerodynamics for use in aeroelastic analyses. The use of these higher order methods provides valuable insight regarding complex flow physics at conditions where linear methods are not theoretically valid. However, the increased computational cost associated with the computation of unsteady aerodynamics and aeroelastic responses using higher order methods has resulted in a subtle change in the manner in which the aeroelastician evaluates and interprets these analyses. First, the increased computational cost of these analyses has tended to dictate a 'snapshot' approach to aeroelastic analyses whereby the aeroelastic response at a handful of dynamic pressures is all that is computed. This 'snapshot' approach is used to identify the flutter dynamic pressure but the actual flutter mechanism is not easily discernible. Second, due to the complexity of the computational methods, methods that could

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“…(1) Generate the number of functions from a selected family of orthogonal functions (Silva 2008) that corresponds to the number of structural modes.…”

Section: Fun3d Reduced-order Modelsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Evaluation of linear, inviscid, viscous, and reduced-order modelling aeroelastic solutions of the AGARD 445.6 wing using root locus analysis

Silva

Chwalowski

Perry

2014

International Journal of Computational Fluid Dynamics

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“…However, with the development of reduced-order modeling (ROM) methods [7,8], the rapid generation of root locus plots using CFD-based unsteady aerodynamics is now available to aeroelasticians. This recently developed technology is being applied to the N+2 supersonic configuration for evaluation of aeroelastic mechanisms across several Mach numbers.…”

Section: Reduced-order Modelsmentioning

confidence: 99%

A Status Review of the Commercial Supersonic Technology (CST) Aeroservoelasticity (ASE) Project

Silva

Sanetrik

Chwalowski

et al. 2016

34th AIAA Applied Aerodynamics Conference

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An overview of recent progress regarding the computational aeroelastic and aeroservoelastic (ASE) analyses of a low-boom supersonic configuration is presented. The overview includes details of the computational models developed to date with a focus on unstructured CFD grids, computational aeroelastic analyses, sonic boom propagation studies that include static aeroelastic effects, and gust loads analyses. In addition, flutter boundaries using aeroelastic Reduced-Order Models (ROMs) are presented at various Mach numbers of interest. Details regarding a collaboration with the Royal Institute of Technology (KTH, Stockholm, Sweden) to design, fabricate, and test a full-span aeroelastic wind-tunnel model are also presented.

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CFD Based Methods for the Computation of Generalized Aerodynamic Forces

Fleischer

Breitsamter

2013

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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Simultaneous Excitation of Multiple-Input/Multiple-Output CFD-Based Unsteady Aerodynamic Systems

Cited by 72 publications

References 22 publications

Evaluation of linear, inviscid, viscous, and reduced-order modelling aeroelastic solutions of the AGARD 445.6 wing using root locus analysis

Evaluation of linear, inviscid, viscous, and reduced-order modelling aeroelastic solutions of the AGARD 445.6 wing using root locus analysis

A Status Review of the Commercial Supersonic Technology (CST) Aeroservoelasticity (ASE) Project

CFD Based Methods for the Computation of Generalized Aerodynamic Forces

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