'Analysis and Application of Advanced Algorithm for Aeronautical Flows' by Spencer Sherwin (ICL)

Duration: 50 mins 32 secs

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'Analysis and Application of Advanced Algorithm for Aeronautical Flows' by Spencer Sherwin (ICL)'s image

Description:	Talk given by Prof Spencer Sherwin (Imperial College London) at Department of Engineering, University of Cambridge, 31 January 2020, as part of the CUED Fluids seminar series.


Created:	2020-02-25 17:50
Collection:	Cambridge Engineering Dept Fluids Seminars
Publisher:	University of Cambridge
Copyright:	Prof Spencer Sherwin
Language:	eng (English)


Abstract:	Advanced high order methods using Spectral/hp element discretization including Galerkin, Discontinuous Galerkin (DG) and Flux Reconstruction (FR) formulations are gaining notable interest in both the academic and industrial sectors. The compact nature of the approach is not only attractive from the perspective of implementation on modern computational hardware but also provides a consistent geometric and spatially localized accuracy unlike many high order finite volume methods. These features make the methodology attractive in complex geometry flows involving transitional and turbulent boundary layers demanding a high level of accuracy for high end engineering applications that commonly arise in the aeronautical sector. In this presentation, we will present our current work on developing a spectral/hp element implicit compressible flow solver for aeronautically related application. The demands of handling “industrial strength” complex geometries at high Reynolds numbers necessarily leads to severe time step restrictions when using explicit time stepping approaches. We have therefore developed a Jacobian-Free-Newton-Krylov (JFNK) implicit solver which makes use of the explicit technique but still require the suitable preconditioners that can be demanding from a memory footprint perspective. After motivating the need for this type of solver we will outline the implementation challenges behind the scheme and demonstrate the suitability of the approach for a number of representative examples.

Abstract:

Advanced high order methods using Spectral/hp element discretization including Galerkin, Discontinuous Galerkin (DG) and Flux Reconstruction (FR) formulations are gaining notable interest in both the academic and industrial sectors. The compact nature of the approach is not only attractive from the perspective of implementation on modern computational hardware but also provides a consistent geometric and spatially localized accuracy unlike many high order finite volume methods. These features make the methodology attractive in complex geometry flows involving transitional and turbulent boundary layers demanding a high level of accuracy for high end engineering applications that commonly arise in the aeronautical sector.

In this presentation, we will present our current work on developing a spectral/hp element implicit compressible flow solver for aeronautically related application. The demands of handling “industrial strength” complex geometries at high Reynolds numbers necessarily leads to severe time step restrictions when using explicit time stepping approaches. We have therefore developed a Jacobian-Free-Newton-Krylov (JFNK) implicit solver which makes use of the explicit technique but still require the suitable preconditioners that can be demanding from a memory footprint perspective. After motivating the need for this type of solver we will outline the implementation challenges behind the scheme and demonstrate the suitability of the approach for a number of representative examples.

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