1,064 research outputs found
A physics-based shock capturing method for unsteady laminar and turbulent flows
We present a shock capturing method for unsteady laminar and turbulent flows. The proposed approach relies on physical principles to increase selected transport coefficients and resolve unstable sharp features, such as shock waves and strong thermal and shear gradients, over the smallest distance allowed by the discretization. In particular, we devise various sensors to detect when the shear viscosity, bulk viscosity and thermal conductivity of the fluid do not suffice to stabilize the numerical solution. In such cases, the transport coefficients are increased as necessary to optimally resolve these features with the available resolution. The performance of the method is illustrated through numerical simulation of external and internal flows in transonic, supersonic, and hypersonic regimes.United States. Air Force. Office of Scientific Research (FA9550-16-1-0214)Pratt & Whitney Aircraft CompanyFundación Obra Social de La CaixaMassachusetts Institute of Technology. Office of the Dean for Graduate Education (Zakhartchenko Fellowship
Subgrid-scale modeling and implicit numerical dissipation in DG-based Large-Eddy Simulation
Over the past few years, high-order discontinuous Galerkin (DG) methods for Large-Eddy Simulation (LES) have emerged as a promising approach to solve complex turbulent flows. However, despite the significant research investment, the relation between the discretization scheme, the subgrid-scale (SGS) model and the resulting LES solver remains unclear. This paper aims to shed some light on this matter. To that end, we investigate the role of the Riemann solver, the SGS model, the time resolution, and the accuracy order in the ability to predict a variety of flow regimes, including transition to turbulence, wall-free turbulence, wall-bounded turbulence, and turbulence decay. The transitional flow over the Eppler 387 wing, the TaylorGreen
vortex problem and the turbulent channel flow are considered to this end. The focus is placed on post-processing the LES results and providing with a rationale for the performance of the various approaches.United States. Air Force. Office of Scientific Research (FA9550-16-1-0214
Implementação e validação de uma abordagem galerkin descontÃnuo para modelagem de turbulância das equações de navier-stokes com média de reynolds (rans) bidimensionais
Orientadores: Marco Lucio Bittencourt, Alberto Costa Nogueira JuniorDissertação (mestrado) - Universidade Estadual de Campinas, Faculdade de Engenharia MecânicaResumo: Uma abordagem de Elementos Finitos Galerkin DescontÃnuo (DG) para as equações de Navier-Stokes com Média de Reynolds (RANS) complementadas pelo modelo Spalart- Allmaras (SA) é implementada e validada para alguns casos de teste básicos. As variáveis de campo do problema são interpoladas usando expansões modais com polinômios de Jacobi. A comunicação entre os elementos é garantida pelo uso dos fluxos numéricos de Roe e HLLC para os termos convectivos e BR1 para os dissipativos. A integração temporal é realizada usando-se um esquema implÃcito Standard-Newton GMRES Backward Euler. O software desenvolvido neste trabalho tem intensivamente usado e expandido o pacote de aplicações para fluidodinâmica da plataforma de código aberto Manticore, de forma a permitir a construção da infraestrutura dos modelos RANSAbstract: A Discontinuous Galerkin Finite Elements (DG) approach for the Reynolds-Averaged Navier-Stokes Equations (RANS) complemented by the closure model Spalart-Allmaras (SA) is implemented and validated for some basic test cases. The problem field vari- ables are interpolated using modal expansions of Jacobi polynomials. The communication between the elements is enforced by using the numerical fluxes Roe and HLLC for the convective terms and BR1 for the dissipative ones. The time-integration is performed by using an implicit Standard-Newton GMRES Backward Euler scheme. The software devel- oped in this work has extensively used and expanded the fluid dynamics toolbox of the open-source framework Manticore in order to construct the infra-structure of the RANS modelsMestradoMecanica dos Sólidos e Projeto MecanicoMestre em Engenharia Mecânic
Implicit time integration for high-order compressible flow solvers
The application of high-order spectral/hp element discontinuous Galerkin (DG)
methods to unsteady compressible flow simulations has gained increasing popularity.
However, the time step is seriously restricted when high-order methods are applied
to an explicit solver. To eliminate this restriction, an implicit high-order compressible flow solver is developed using DG methods for spatial discretization, diagonally
implicit Runge-Kutta methods for temporal discretization, and the Jacobian-free
Newton-Krylov method as its nonlinear solver. To accelerate convergence, a block
relaxed Jacobi preconditioner is partially matrix-free implementation with a hybrid
calculation of analytical and numerical Jacobian.The problem of too many user-defined parameters within the implicit solver is
then studied. A systematic framework of adaptive strategies is designed to relax the
difficulty of parameter choices. The adaptive time-stepping strategy is based on the
observation that in a fixed mesh simulation, when the total error is dominated by the
spatial error, further decreasing of temporal error through decreasing the time step
cannot help increase accuracy but only slow down the solver. Based on a similar
error analysis, an adaptive Newton tolerance is proposed based on the idea that
the iterative error should be smaller than the temporal error to guarantee temporal
accuracy. An adaptive strategy to update the preconditioner based on the Krylov
solver’s convergence state is also discussed. Finally, an adaptive implicit solver is
developed that eliminates the need for repeated tests of tunning parameters, whose
accuracy and efficiency are verified in various steady/unsteady simulations. An improved shock-capturing strategy is also proposed when the implicit solver
is applied to high-speed simulations. Through comparisons among the forms of
three popular artificial viscosities, we identify the importance of the density term
and add density-related terms on the original bulk-stress based artificial viscosity.
To stabilize the simulations involving strong shear layers, we design an extra shearstress based artificial viscosity. The new shock-capturing strategy helps dissipate
oscillations at shocks but has negligible dissipation in smooth regions.Open Acces
Computational fluid dynamics for aerospace propulsion systems: an approach based on discontinuous finite elements
The purpose of this work is the development of a numerical tool devoted to the
study of the flow field in the components of aerospace propulsion systems. The
goal is to obtain a code which can efficiently deal with both steady and unsteady
problems, even in the presence of complex geometries.
Several physical models have been implemented and tested, starting from Euler
equations up to a three equations RANS model. Numerical results have been compared
with experimental data for several real life applications in order to understand
the range of applicability of the code. Performance optimization has been
considered with particular care thanks to the participation to two international
Workshops in which the results were compared with other groups from all over the
world.
As far as the numerical aspect is concerned, state-of-art algorithms have been implemented
in order to make the tool competitive with respect to existing softwares.
The features of the chosen discretization have been exploited to develop adaptive
algorithms (p, h and hp adaptivity) which can automatically refine the discretization.
Furthermore, two new algorithms have been developed during the research
activity. In particular, a new technique (Feedback filtering [1]) for shock capturing
in the framework of Discontinuous Galerkin methods has been introduced. It is
based on an adaptive filter and can be efficiently used with explicit time integration
schemes. Furthermore, a new method (Enhance Stability Recovery [2]) for
the computation of diffusive fluxes in Discontinuous Galerkin discretizations has
been developed. It derives from the original recovery approach proposed by van
Leer and Nomura [3] in 2005 but it uses a different recovery basis and a different
approach for the imposition of Dirichlet boundary conditions. The performed numerical
comparisons showed that the ESR method has a larger stability limit in
explicit time integration with respect to other existing methods (BR2 [4] and original
recovery [3]). In conclusion, several well known test cases were studied in order
to evaluate the behavior of the implemented physical models and the performance
of the developed numerical schemes
ScaleResolving Simulations of a Fundamental TrailingEdge Cooling Slot Using a DiscontinuousGalerkin SpectralElement Method
The accurate prediction of turbulent mixing in high-pressure turbines that incorporate various airfoil surface-cooling strategies is becoming increasing critical to the design of modern gas turbine engines where the quest for improved efficiency is driving compressor overall pressure ratios and turbine inlet temperatures to much higher levels than ever before. In the present paper, a recently developed computational capability for accurate and efficient scaleresolving simulations of turbomachinery is extended to study the turbulent mixing mechanism of a simplified abstraction of an airfoil trailing-edge cooling slot - a plane wall jet with finite lip thickness discharging into an ambient flow. The computational capability is based on an entropy stable, discontinuousGalerkin approach that extends to arbitrarily high orders of spatial and temporal accuracy. The numerical results show that the present simulations capture the trends observed in the experiments. Discrepancies between the simulations and experiments are believed to be due to differences in the inflow profiles and tunnel sidewall effects. The thick lip configuration leads to a thicker wake and higher unsteadiness in the wall jet compared to the thin lip. A detailed comparison of the turbulent flowfields is presented to highlight differences arising due to lip thickness variations
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