A Segregated Finite Element Method for Thermo-chemical Non-equilibrium Hypersonic Flows on Adaptive Grids PDF Download
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Author: Djaffar Ait-Ali-Yahia
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Djaffar Ait-Ali-Yahia
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Djaffar Ait-Ali-Yahia
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 0
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This dissertation concerns the development of a loosely coupled, finite element method for the numerical simulation of 2-D hypersonic, thermo-chemical equilibrium and nonequilibrium flows, with an emphasis on resolving directional flow features, such as shocks, by an anisotropic mesh adaptation procedure. Since the flow field of such problems is chemically reacting and molecular species are vibrationally excited, numerical analyses based on an ideal gas assumption result in inaccurate if not erroneous solutions. Instead, hypersonic flows must be computed by solving the gasdynamic equations in conjunction with species transport and vibrational energy equations. The number of species transport equations could be very high but is drastically reduced by neglecting the ionization, thus leaving one to represent the air by only five neutral species: O, N, NO, O$\sb2$ and N$\sb2.$ This system of equations is further simplified by considering an algebraic equation for conservation of the fixed nitrogen to oxygen ratio in air. The chemical source terms are computed according to kinetic models, with reaction rate coefficients given by Park's reaction models. All molecular species are characterized by a single vibrational temperature, yielding the well-known two-temperature thermal model which requires the solution of a single conservation equation for the total vibrational energy. In this thesis, the governing equations are decoupled into three systems of PDEs--gasdynamic, chemical and vibrational systems--which are integrated by an implicit time-marching technique and discretized in space by a Galerkin-finite element method. This loosely-coupled formulation maintains the robustness of implicit techniques, while keeping the memory requirements to a manageable level. It also allows each system of PDEs to be integrated by the most appropriate algorithm to achieve the best global convergence. This particular feature makes a partially-decoupled formulation attractive for the extension of existing gasdynamic codes to hypersonic nonequilibrium flow problems, as well as for other applications having stiff source terms. The hypersonic shocks are resolved in a cost-effective manner by coupling the flow solver to a directionally mesh adaptive scheme using an edge-based error estimate and an efficient mesh movement strategy. The accuracy of the numerical solution is continuously evaluated using a bound available from finite element theory. The Hessian (matrix of second derivatives) of a selected variable is numerically computed and then modified by taking the absolute value of its eigenvalues to finally produce a Riemannian metric. Using elementary differential geometry, the edge-based error estimate is thus defined as the length of the element edges in this Riemannian metric. This error is then equidistributed over the mesh edges by applying a mesh movement scheme made efficient by removing the usual constraints on grid orthogonality. The construction of an anisotropic mesh may thus be interpreted as seeking a uniform mesh in the defined metric. The overall methodology is validated on various relevant benchmarks, ranging from supersonic frozen flows to hypersonic thermo-chemical nonequilibrium flows, and the results are compared against experimental data and, when not possible, to other computational approaches.
Author: Benjamin S. Kirk
Publisher: BiblioGov
ISBN: 9781289131937
Category :
Languages : en
Pages : 38
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Presentation topics include background and motivation; physical modeling including governing equations and thermochemistry; finite element formulation; results of inviscid thermal nonequilibrium chemically reacting flow and viscous thermal equilibrium chemical reacting flow; and near-term effort.
Author: Sean R. Copeland
Publisher:
ISBN:
Category :
Languages : en
Pages :
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This thesis explores the formulation, derivation, and implementation of the continuous adjoint equations for hypersonic, nonequilibrium flow environments. The adjoint method is an efficient means for acquiring sensitivity information that can be used in a gradient-based framework to perform optimal shape design of aerospace systems. A solution to the adjoint system of equations carries a computational cost roughly equal to a single solution of the flow governing equations, regardless of the dimensionality of the design space. When compared to other gradient acquisition methods, where computational costs scale with design space dimensionality, the adjoint method is superior when the dimensionality is high and when solutions to the governing equations are expensive. Such conditions are often representative of most aerospace problems of practical interest. In addition to providing gradient information, solutions to the adjoint equations may be used as 'sensors' or 'weighting factors' to perform error estimation and adaptive mesh refinement. Hypersonic systems operate in unique flow environments that are dominated by chemical and thermodynamic phenomena not observed at lower Mach numbers. Accurate simulations of these environments require sophisticated thermochemical models to resolve atomic-scale physical processes that have first-order effects on integrated vehicle performance metrics, including lift, drag, stability, controllability, and heat transfer. Because of the computational expense demanded by these high-fidelity tools, the conceptual vehicle design process often relies heavily on low- to medium-fidelity, correlation-based tools that are confined to narrow regions of applicability. As a consequence, the hypersonic vehicle design process has remained relatively static for the past several decades. The adjoint method enables the use of high-fidelity tools early in the design cycle of hypersonic systems, and is a transformative technology for the hypersonic community. This work provides the first derivation, implementation, and verification of the continuous adjoint equations for hypersonic flow environments in thermochemical nonequilibrium. Appropriate boundary conditions and surface sensitivities are provided for both projected force and thermal objective functions for continuum, viscous, multi-component gas mixtures. The adjoint system is implemented in a second-order, unstructured, finite-volume-method (FVM) flow solver that is representative of the state-of-the-art in high-fidelity aerothermodynamic analysis for hypersonic entry systems. Gradients from the adjoint-derived surface sensitivities are verified against gradients calculated using a finite-difference methodology for several representative geometries relevant to ballistic and lifting-body entry vehicles.
Author: American Institute of Aeronautics and Astronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1304
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Author: Paul Kutler
Publisher: Springer
ISBN: 9783540630548
Category : Science
Languages : en
Pages : 680
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This book covers a wide area of topics, from fundamental theories to industrial applications. It serves as a useful reference for everyone interested in computational modeling of partial differential equations pertinent primarily to aeronautical applications. The reader will find three survey articles on the present state of the art in numerical simulation of the transition to turbulence, in design optimization of aircraft configurations, and in turbulence modeling. These are followed by carefully selected and refereed articles on algorithms and their applications, on design methods, on grid adaption techniques, on direct numerical simulations, and on parallel computing, and much more.
Author: Michael John Aftosmis
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 292
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The use of unstructured, adaptive, embedded grids has been applied to hypersonic nonequilibrium CFD problems. Grid adaptation was accomplished by sub-dividing computational cells for 2-D and axisymmetric blunt body configurations. The high temperature gas mixture was described by Lighthill's dissociating gas model which was extended to include multiple coupled reaction paths in both viscous and inviscid flows. Ni's finite volume Lax-Wendroff scheme was used to integrate the governing equations. This algorithm was extended to include shock fitting and adaptation on general, unstructured, time dependent grids. The explicit real-gas algorithm and shock fitting procedure were validated by comparisons with experimental and computational results for perfect gas, dissociating gas, and multiple reaction cases. These comparisons also emphasized the importance of chemical length scale effects in predicting nonequilibrium gas behavior. Such effects were linked not only to species concentration profiles throughout the shock layer, but also to the excess production of Nitric Oxide frequently reported off the symmetry plane in reacting air blunt body flows. A detailed study of basic nonequilibrium flow phenomena has been completed for freestream Mach numbers from 10 to 15 over blunted cones and wedges. These flows demonstrated degrees of nonequilibrium ranging from nearly frozen to near equilibrium. In all cases the adaptive procedure correctly located and resolved perfect gas and nonequilibrium features. Adaptation was shown to be particularly useful in capturing the steep chemical gradients which appear within the shock layer. (jhd).
Author: Ankush Bhatia
Publisher:
ISBN:
Category :
Languages : en
Pages : 192
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This methodology requires no a priori knowledge of the shock0s location, and is suitable for detached shock problems. r-p adaptivity method has allowed for successful prediction of surface heating rate for hypersonic flow over cylinder. Additionally, good comparisons are made, for non-equilibrium hypersonic flows, to the published results. This tool is also used to determine the effect of micro-second pulsed sinusoidal Dielectric Barrier Discharge (DBD) plasma actuators on the surface heating reduction for hypersonic flow over cylinder. A significant effect, of the plasma actuators, is found on the surface heating for hypersonic flows (with and without thermo-chemistry) and several designs are investigated for optimum heating reduction.
Author: Christian Windisch
Publisher:
ISBN: 9783954047550
Category :
Languages : en
Pages : 214
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 934
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