Adjoint - based Aeroacoustic Design Optimization for Blade Vortex Interaction Noise

Fabiano, Enrico; Mavriplis, Dimitri J.; Sitaraman, Jayanarayanan

doi:10.2514/6.2015-1801

Cited by 5 publications

(3 citation statements)

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“…In future design and optimization applications, the trim control parameters will be updated through constraint optimization procedures. 16,25 In Section III.A, a verification study is conducted to demonstrate the accuracy of the current F/D loose and tight coupling procedures for the HART-II baseline rotorcraft configuration. 7…”

Section: B Cfd/ca Coupling Approachesmentioning

confidence: 99%

“…15 In contrast with the finite-difference methods employing real-valued perturbations, the complex-variable approach does not suffer from subtractive error cancellation and is capable of producing the true sensitivity of the discrete solution with respect to a chosen design parameter. Recently, adjoint-based sensitivity analyses of model rotorcraft simulations 11,16,17 have been demonstrated to guide design and optimization.…”

Section: Introductionmentioning

confidence: 99%

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Sensitivity Analysis of Multidisciplinary Rotorcraft Simulations

Wang

Diskin

Biedron

et al. 2017

55th AIAA Aerospace Sciences Meeting

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A multidisciplinary sensitivity analysis of rotorcraft simulations involving tightly coupled high-fidelity computational fluid dynamics and comprehensive analysis solvers is presented and evaluated. An unstructured sensitivity-enabled Navier-Stokes solver, FUN3D, and a nonlinear flexible multibody dynamics solver, DY-MORE, are coupled to predict the aerodynamic loads and structural responses of helicopter rotor blades. A discretely-consistent adjoint-based sensitivity analysis available in FUN3D provides sensitivities arising from unsteady turbulent flows and unstructured dynamic overset meshes, while a complex-variable approach is used to compute DYMORE structural sensitivities with respect to aerodynamic loads. The multidisciplinary sensitivity analysis is conducted through integrating the sensitivity components from each discipline of the coupled system. Numerical results verify accuracy of the FUN3D/DYMORE system by conducting simulations for a benchmark rotorcraft test model and comparing solutions with established analyses and experimental data. Complex-variable implementation of sensitivity analysis of DYMORE and the coupled FUN3D/DYMORE system is verified by comparing with real-valued analysis and sensitivities. Correctness of adjoint formulations for FUN3D/DYMORE interfaces is verified by comparing adjoint-based and complex-variable sensitivities. Finally, sensitivities of the lift and drag functions obtained by complex-variable FUN3D/DYMORE simulations are compared with sensitivities computed by the multidisciplinary sensitivity analysis, which couples adjoint-based flow and grid sensitivities of FUN3D and FUN3D/DYMORE interfaces with complex-variable sensitivities of DYMORE structural responses.

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Section: B Cfd/ca Coupling Approachesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Sensitivity Analysis of Multidisciplinary Rotorcraft Simulations

Wang

Diskin

Biedron

et al. 2017

55th AIAA Aerospace Sciences Meeting

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“…In previous work (Ref. 7) we demonstrated the feasibility of unsteady aeroacoustic optimization by developing the coupled adjoint aeroacoustic sensitivity used to drive the gradient-based shape optimization of a two-dimensional airfoil in blade vortex interaction. We then extended our formulation to the noise minimization of a rigid helicopter rotor in trimmed forward flight (Ref.…”

Section: Introductionmentioning

confidence: 99%

Adjoint-Based Aeroacoustic Design-Optimization of Flexible Rotors in Forward Flight

Fabiano¹,

Mavriplis²

2017

j am helicopter soc

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This paper presents the development and application of a time-dependent adjoint-based method for aeroacoustic design optimization of flexible helicopter rotors in forward flight. The rotor noise signature at a farfield observer is computed with the hybrid aeroacoustic approach in which a near-body coupled computational fluid dynamics/computational structural dynamics solver provides flow and geometry data to an FW-H acoustic module that propagates the acoustic waves to a farfield observer. Forward and adjoint sensitivity formulations are derived that correspond to analogues of the multidisciplinary flexible aeroacoustic analysis problem. The newly implemented aeroacoustic capability is first verified to effectively perform forward flight noise prediction by comparison with the PSU-WOPWOP acoustic tool. Upon successful validation, a gradient based optimization method is used to minimize the required torque of the flexible HART-II rotor in trimmed forward flight while reducing the acoustic signature at a farfield observer by changing the shape of the blades. The adjoint formulation developed in this work is used to efficiently compute the sensitivity required by the optimization algorithm.

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