By Richard A. Shapiro (auth.), Richard A. Shapiro (eds.)
This monograph is the results of my PhD thesis paintings in Computational Fluid Dynamics on the Massachusettes Institute of know-how lower than the supervision of Professor Earll Murman. a brand new finite point al gorithm is gifted for fixing the regular Euler equations describing the movement of an inviscid, compressible, excellent gasoline. This set of rules makes use of a finite aspect spatial discretization coupled with a Runge-Kutta time integration to sit back to regular country. it's proven that different algorithms, akin to finite distinction and finite quantity tools, should be derived utilizing finite aspect ideas. A higher-order biquadratic approximation is brought. numerous try difficulties are computed to ensure the algorithms. Adaptive gridding in and 3 dimensions utilizing quadrilateral and hexahedral components is built and validated. edition is proven to supply CPU mark downs of an element of two to sixteen, and biquadratic parts are proven to supply power reductions of an element of two to six. An research of the dispersive homes of a number of discretization equipment for the Euler equations is gifted, and effects permitting the prediction of dispersive blunders are received. The adaptive set of rules is utilized to the answer of a number of flows in scramjet inlets in and 3 dimensions, demonstrat ing a number of the various physics linked to those flows. a few matters within the layout and implementation of adaptive finite aspect algorithms on vector and parallel pcs are discussed.
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Additional info for Adaptive Finite Element Solution Algorithm for the Euler Equations
2 Verification and Comparison of Methods This section compares and verifies the Galerkin, cell-vertex, and central difference finite element methods. 03. 1 5° Converging Channel This test case is the flow through a channel with Moo = 2 and the bottom wall sloped at 5°. 3 shows the geometry of the channel. This problem was computed using the three methods on a coarse and fine grid. The coarse grid is shown in Fig. 4, and is 40x10 elements. The fine grid is BOx20 elements. 1 shows the values of pressure, density and Mach number for the exact solution in each of the five regions of the flow.
5 flow over a 10% cosine-squared bump was computed on a 24x8 biquadratic mesh and a 60x20 bilinear mesh. 43 shows contours of density for the biquadratic elements. The contours are quite symmetric, as one would expect from a flow which remains completely subsonic. Most of the non-smoothness seen in the contours is introduced by the plot package (which divided each biquadratic element into 32 linear triangles), rather than actual errors in the flow. For comparison, Fig. 44 shows these contours in the bilinear case.
The geometry for this case is shown in Fig. 2.