Using FUN3D for Aeroelatic, Sonic Boom, and AeroPropulsoServoElastic (APSE) Analyses of a Supersonic Configuration

Silva, Walter A.; Sanetrik, Mark D.; Chwalowski, Pawel

doi:10.2514/6.2016-1319

Cited by 10 publications

(5 citation statements)

References 7 publications

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“…Leveraging symmetry, a modal solution was performed on the FEM semispan by properly defining boundary conditions [2,8,19]. The symmetric modes of the vehicle provide adequate coupling for the propulsion system for this sensitivity analysis, which is not investigating off-nominal thrust asymmetries.…”

Section: Vehicle Modelmentioning

confidence: 99%

“…The primary advancement to the aeroelasticity field developed here is the integration of a nonlinear dynamic model of a propulsion system into an elastic vehicle model, which enables sensitivity studies exploring broadened coupling effects. The combination of the aeroelastic (AE) and propulsion system interactions is referred to as aero-propulsoelastic (APE) [8]. APE considerations have the potential to impact the propulsion system performance and vehicle structural deformations, which can also impact the sonic boom noise signature.…”

mentioning

confidence: 99%

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Aero-Propulso-Elastic Analysis of a Supersonic Transport

Connolly¹,

Kopasakis²,

Chwalowski³

et al. 2020

Journal of Aircraft

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An aeroelastic modeling capability of a flexible aircraft with gas turbine engines is developed using a computational fluid dynamics tool as an integration platform. The new modeling capability allows for the typical aeroelastic analysis to include a nonlinear dynamic model of the turbomachinery that is capable of capturing relevant gas dynamics. An example case of the aero-propulso-elastic (APE) modeling capability is explored for a supersonic transport vehicle with turbofan engines. An overview of the methodology for integrating the propulsion system and elastic vehicle is provided. This is followed by a study to explore coupling sensitivities compared against typical aeroelastic analysis. Dynamic and static vehicle responses are considered across key flight conditions and vehicle-level angles of attack, where the inclusion of the propulsion system has a 10% increase in vehicle wing tip deformations. It is found that the propulsion system is stable at various operating conditions, with structural oscillations having little impact on propulsion system performance. Perceived loudness, a key performance metric for a supersonic transport, is investigated using the APE model. Results lead to an approximately 4 dB increase in noise over a rigid body analysis that neglects the propulsion system. The greatest impacts are shown during off-nominal conditions.

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Section: Vehicle Modelmentioning

confidence: 99%

mentioning

confidence: 99%

Aero-Propulso-Elastic Analysis of a Supersonic Transport

Connolly¹,

Kopasakis²,

Chwalowski³

et al. 2020

Journal of Aircraft

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“…FUN3D is a node-centered, unstructured-grid RANS solver, which is widely used for high-fidelity analysis and adjoint-based design of complex turbulent flows. [27][28][29][30][31][32] Two different discretizations available in FUN3D are employed: the baseline finite-volume discretization (FUNFV) and a recently implemented stabilized finite-element discretization (SFE) based on a Streamlined Upwind Petrov-Galerkin formulation. 33 FUNFV discretizes the governing flow equations on mixed-element grids; the elements are tetrahedra, pyramids, prisms, and hexahedra.…”

Section: Iia Fun3dmentioning

confidence: 99%

Grid Convergence for Three Dimensional Benchmark Turbulent Flows

Diskin

Anderson

Pandya

et al. 2018

2018 AIAA Aerospace Sciences Meeting

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Grid convergence studies are performed to establish reference solutions for benchmark three dimensional turbulent flows in support of the ongoing turbulence model verification and validation effort at the Turbulence Modeling Resource website curated by NASA. The benchmark cases are a subsonic flow around a hemisphere cylinder and a transonic flow around the ONERA M6 wing with a sharp trailing edge. The study applies widely-used computational fluid dynamics codes developed and supported at the NASA Langley Research Center: FUN3D, USM3D, and CFL3D. Reference steady-state solutions are computed for the Reynolds-Averaged Navier-Stokes equations with the Spalart-Allmaras turbulence model on families of consistently-refined grids composed of different types of cells. Coarse-to-fine and code-to-code solution variation is described in detail.

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“…This is particularly an issue as more detailed analysis requires models of higher fidelity and more analyses are coupled in a multidisciplinary environment. 13 These models may have a significant amount of uncertainty and propagating it can be challenging even by using recent approaches for improved efficiency. 14 However, many of these uncertainties are common to models of lower fidelity, though their impact may be different.…”

Section: Introductionmentioning

confidence: 99%

Multifidelity Uncertainty Quantification of a Commercial Supersonic Transport

West

Phillips

2018

2018 Applied Aerodynamics Conference

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The objective of this work was to develop a multifidelity uncertainty quantification approach for efficient analysis of a commercial supersonic transport. An approach based on non-intrusive polynomial chaos was formulated in which a low-fidelity model could be corrected by any number of high-fidelity models. The formulation and methodology also allows for the addition of uncertainty sources not present in the lower fidelity models. To demonstrate the applicability of the multifidelity polynomial chaos approach, two model problems were explored. The first was supersonic airfoil with three levels of modeling fidelity, each capturing an additional level of physics. The second problem was a commercial supersonic transport. This model had three levels of fidelity that included two different modeling approaches and the addition of physics between the fidelity levels. Both problems illustrate the applicability and significant computational savings of the multifidelity polynomial chaos method.

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Using FUN3D for Aeroelatic, Sonic Boom, and AeroPropulsoServoElastic (APSE) Analyses of a Supersonic Configuration

Cited by 10 publications

References 7 publications

Aero-Propulso-Elastic Analysis of a Supersonic Transport

Aero-Propulso-Elastic Analysis of a Supersonic Transport

Grid Convergence for Three Dimensional Benchmark Turbulent Flows

Multifidelity Uncertainty Quantification of a Commercial Supersonic Transport

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