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• W2981371083 abstract "Computational aerothermodynamics is the branch of science which focuses on thecomputation of the effect of thermodynamic and transport models on aerodynamicsand heating. They are widely used for external ow cases. On the other hand, thecomputation of heat and stress in the design of Nano/Micro Electronic MechanicalSystems from the point of view of a Fluid mechanics engineer is also an important areaof study. A generalized computational tool which can simulate the low and high speedflows at both the macro and micro levels is desirable from the perspective of industry,academics and research. For a developing nation, it is extremely important to havesuch a solver developed indigenously to create self-sufficiency and self-reliance.In this work, a robust three-dimensional density-based general purpose computationalfluid dynamics solver was developed in house by our research group. The cell centredfinite volume discretization method is used on an unstructured grid, whichis more desirable for computation on a complex geometry from the perspective ofpre-processing (meshing). Compressible ow solutions obtained from density-basedsolvers usually do not work well at low speeds where the ow is close to incompressible,unless special schemes and/or special treatments are used. An all-speedalgorithm was incorporated using two different methods: (a) preconditioning of thegoverning equations or (b) through the use of the recently developed SLAU2 all speedconvective scheme. The time-stepping discretization is done implicitly, usingthe lower-upper symmetric-Gauss-Seidel method, which allows us to take a high CFLnumber during computations. Throughout this work, we have used a second-orderaccurate reconstruction with limiters to accurately capture the shocks without dispersiveerror. Turbulence modelling is done using Favre- and Reynolds- AveragedNavier-Stokes equations using the Spalart Allmaras turbulence model.The developed solver is used to solve external ow problems at low and high speeds(hypersonic regimes). In these problems, the thesis focus is on the implementation andtesting of an automatic wall function treatment for the Spalart-Allmaras turbulencemodel.The applicability of the solver is extended to rarefied gas ow regimes in thefollowing manner. Thermal non-equilibrium which exists in the rarefied ow regimeis tackled using non-equilibrium boundary conditions in the slip ow regime. The useof non-equilibrium boundary conditions allows the applicability of the Navier-Stokesequation to be extended beyond the continuum to the slip regime. This approachis used to solve problems of hypersonic rarefied flows and nano/micro flows; and fortesting and validation of several recently proposed boundary conditions for severalproblems in the slip ow regime.The main focus of this work is in developing newer numerical methods and ontesting and improving other recently proposed numerical techniques that are used forsolving the problems covered in this thesis. In the following paragraphs we presentthe major outcomes of the thesis.The Spalart-Allmaras (SA) is one of the most popular turbulence models in theaerospace CFD community. In its original (low-Reynolds number) formulation itrequires a very tight grid (with y+ ' 1) spacing near the wall to resolve the high owgradients. The use of _ne grids increases the computational cost of the solutions.However, the use of wall functions with an automatic feature of switching from thewall function to the low-Reynolds number approach is an effective solution to thisproblem. We have extended Menter's automatic wall treatment (AWT), devised forthe K" @default.
• W2981371083 created "2019-11-01" @default.
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• W2981371083 date "2019-01-01" @default.
• W2981371083 modified "2023-09-24" @default.
• W2981371083 title "Development of an Unstructured CFD Solver for External Aerothermodynamics and Nano/Micro Flows" @default.
• W2981371083 hasPublicationYear "2019" @default.
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