1,036 research outputs found
Modal and transient dynamics of jet flows
International audienceThe linear stability dynamics of incompressible and compressible isothermal jets are investigated by means of their optimal initial perturbations and of their temporal eigenmodes. The transient growth analysis of optimal perturbations is robust and allows physical interpretation of the salient instability mechanisms. In contrast, the modal representation appears to be inadequate, as neither the computed eigenvalue spectrum nor the eigenmode shapes allow a characterization of the flow dynamics in these settings. More surprisingly, numerical issues also prevent the reconstruction of the dynamics from a basis of computed eigenmodes. An investigation of simple model problems reveals inherent problems of this modal approach in the context of a stable convection-dominated configuration. In particular, eigenmodes may exhibit an exponential growth in the streamwise direction even in regions where the flow is locally stable
Verification of Unstructured Grid Adaptation Components
Adaptive unstructured grid techniques have made limited impact on production analysis workflows where the control of discretization error is critical to obtaining reliable simulation results. Recent progress has matured a number of independent implementations of flow solvers, error estimation methods, and anisotropic grid adaptation mechanics. Known differences and previously unknown differences in grid adaptation components and their integrated processes are identified here for study. Unstructured grid adaptation tools are verified using analytic functions and the Code Comparison Principle. Three analytic functions with different smoothness properties are adapted to show the impact of smoothness on implementation differences. A scalar advection-diffusion problem with an analytic solution that models a boundary layer is adapted to test individual grid adaptation components. Laminar flow over a delta wing and turbulent flow over an ONERA M6 wing are verified with multiple, independent grid adaptation procedures to show consistent convergence to fine-grid forces and a moment. The scalar problems illustrate known differences in a grid adaptation component implementation and a previously unknown interaction between components. The wing adaptation cases in the current study document a clear improvement to existing grid adaptation procedures. The stage is set for the infusion of verified grid adaptation into production fluid flow simulations
Methodology for sensitivity analysis, approximate analysis, and design optimization in CFD for multidisciplinary applications
Fundamental equations of aerodynamic sensitivity analysis and approximate analysis for the two dimensional thin layer Navier-Stokes equations are reviewed, and special boundary condition considerations necessary to apply these equations to isolated lifting airfoils on 'C' and 'O' meshes are discussed in detail. An efficient strategy which is based on the finite element method and an elastic membrane representation of the computational domain is successfully tested, which circumvents the costly 'brute force' method of obtaining grid sensitivity derivatives, and is also useful in mesh regeneration. The issue of turbulence modeling is addressed in a preliminary study. Aerodynamic shape sensitivity derivatives are efficiently calculated, and their accuracy is validated on two viscous test problems, including: (1) internal flow through a double throat nozzle, and (2) external flow over a NACA 4-digit airfoil. An automated aerodynamic design optimization strategy is outlined which includes the use of a design optimization program, an aerodynamic flow analysis code, an aerodynamic sensitivity and approximate analysis code, and a mesh regeneration and grid sensitivity analysis code. Application of the optimization methodology to the two test problems in each case resulted in a new design having a significantly improved performance in the aerodynamic response of interest
Mesh-Free Hydrodynamic Stability
A specialized mesh-free radial basis function-based finite difference
(RBF-FD) discretization is used to solve the large eigenvalue problems arising
in hydrodynamic stability analyses of flows in complex domains. Polyharmonic
spline functions with polynomial augmentation (PHS+poly) are used to construct
the discrete linearized incompressible and compressible Navier-Stokes operators
on scattered nodes. Rigorous global and local eigenvalue stability studies of
these global operators and their constituent RBF stencils provide a set of
parameters that guarantee stability while balancing accuracy and computational
efficiency. Specialized elliptical stencils to compute boundary-normal
derivatives are introduced and the treatment of the pole singularity in
cylindrical coordinates is discussed. The numerical framework is demonstrated
and validated on a number of hydrodynamic stability methods ranging from
classical linear theory of laminar flows to state-of-the-art non-modal
approaches that are applicable to turbulent mean flows. The examples include
linear stability, resolvent, and wavemaker analyses of cylinder flow at
Reynolds numbers ranging from 47 to 180, and resolvent and wavemaker analyses
of the self-similar flat-plate boundary layer at a Reynolds number as well as
the turbulent mean of a high-Reynolds-number transonic jet at Mach number 0.9.
All previously-known results are found in close agreement with the literature.
Finally, the resolvent-based wavemaker analyses of the Blasius boundary layer
and turbulent jet flows offer new physical insight into the modal and non-modal
growth in these flows
SOLID-SHELL FINITE ELEMENT MODELS FOR EXPLICIT SIMULATIONS OF CRACK PROPAGATION IN THIN STRUCTURES
Crack propagation in thin shell structures due to cutting is conveniently simulated
using explicit finite element approaches, in view of the high nonlinearity of the problem. Solidshell
elements are usually preferred for the discretization in the presence of complex material
behavior and degradation phenomena such as delamination, since they allow for a correct
representation of the thickness geometry. However, in solid-shell elements the small thickness
leads to a very high maximum eigenfrequency, which imply very small stable time-steps. A new
selective mass scaling technique is proposed to increase the time-step size without affecting
accuracy. New ”directional” cohesive interface elements are used in conjunction with selective
mass scaling to account for the interaction with a sharp blade in cutting processes of thin ductile
shells
Entropy stable wall boundary conditions for the three-dimensional compressible Navier-Stokes equations
Non-linear entropy stability and a summation-by-parts framework are used to
derive entropy stable wall boundary conditions for the three-dimensional
compressible Navier--Stokes equations. A semi-discrete entropy estimate for the
entire domain is achieved when the new boundary conditions are coupled with an
entropy stable discrete interior operator. The data at the boundary are weakly
imposed using a penalty flux approach and a simultaneous-approximation-term
penalty technique. Although discontinuous spectral collocation operators on
unstructured grids are used herein for the purpose of demonstrating their
robustness and efficacy, the new boundary conditions are compatible with any
diagonal norm summation-by-parts spatial operator, including finite element,
finite difference, finite volume, discontinuous Galerkin, and flux
reconstruction/correction procedure via reconstruction schemes. The proposed
boundary treatment is tested for three-dimensional subsonic and supersonic
flows. The numerical computations corroborate the non-linear stability (entropy
stability) and accuracy of the boundary conditions.Comment: 43 page
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