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diff --git a/Master/texmf-dist/doc/latex/aiaa/pre2004/demos/talk/smptalk.tex b/Master/texmf-dist/doc/latex/aiaa/pre2004/demos/talk/smptalk.tex new file mode 100644 index 00000000000..4dba1b85ff5 --- /dev/null +++ b/Master/texmf-dist/doc/latex/aiaa/pre2004/demos/talk/smptalk.tex @@ -0,0 +1,296 @@ +% +% 'smptalk.tex' sample slide presentation - courtesy of karen bibb +% +% typical (unix) processing sequence for postscript printer: +% +% latex smptalk - create dvi file +% xdvi -paper usr smptalk - preview dvi file +% dvips -t landscape smptalk - transform dvi file to postscript +% ghostview -landscape -swap smptalk.ps - check postscript output +% lpr smptalk.ps - print postscript file + +\documentclass[landscape]{slides} + +% load custom command definitions and other default settings: +\usepackage{smptalk} + +% un-comment for ``page'' numbers: +%\pagestyle{plain} + +% un-comment for processing only a select few slides or notes: +%\onlyslides{1-2,5,10-999} +%\onlynotes{1-2,12} +% or, for interactive prompting, un-comment the following: +%\typein[\slides]{Which slides to do?} +%\onlyslides{\slides} +%\onlynotes{\slides} + +\begin{document} + +\begin{slide}\typeout{Title:} + \begin{center} + {\Large\bf Hypersonic Flow Computations On Unstructured Meshes} + + {\large\bf AIAA 97--0625} + + \begin{tabular}{cc} + K. L. Bibb & J. Peraire \\[.1in] + \it NASA Langley Research & \it Massachusetts Institute \\ + \it Center & \it of Technology \\ + \it Hampton, Virginia & \it Cambridge, Massachusetts + \end{tabular} + + C. J. Riley \\[.1in] + \it NASA Langley Research Center \\ + Hampton, Virginia + \end{center} +\end{slide} + +\begin{note} + \begin{describe}[1.5in] + \item [Session] Applied Computational Aero + \item [Time] wed afternoon + \item [Mention] colleagues + \begin{items} + \item Ram Prabhu for running codes + \item Bill Scallion \& Matt Rhode for UPWT data + \end{items} + \end{describe} +\end{note} + +\begin{slide}\typeout{Background:} + \title{Background} + \begin{items} + \item Rapid, accurate aerodynamic screening capability is + needed: + \begin{items} + \item aerodynamic performance coefficients + \item pressure loads for preliminary structural analysis + \item general flow features, for example, shock location + \end{items} + \item Unstructured grids offer flexible and rapid grid generation + \item Historically, unstructured Euler schemes + are not robust hypersonically + \end{items} +\end{slide} + +\begin{slide}\typeout{Outline:} + \title{Outline} + \leftmargin 3in + \begin{items} + \item Computational algorithm + \item Comparisons to other codes\\ + and experiment + \item Use as a screening tool + \item Concluding remarks + \end{items} +\end{slide} + +\begin{note} + \begin{items} + \item details are in the paper for the algorithm + \item screening tools are talked about throughout + \end{items} +\end{note} + +\begin{slide}\typeout{Flow solver (overview):} + \title{FELISA System} + \begin{items} + \item Unstructured mesh generation + \item `Standard' Euler flow solver, + for subsonic $\Rightarrow$ low supersonic + \item Hypersonic Euler flow solver, FELISA\_HYP + \begin{items} + \item perfect gas + \item equilibrium air + \item CF$_4$ + \end{items} + \item Parallel versions of flow solvers + \end{items} +\end{slide} + +\begin{note} + \begin{items} + \item for parallel: work on IBM sP2, J90, workstation clusters. + \item not used for the calculations in the paper + \end{items} +\end{note} + +\begin{slide}\typeout{Flow solver (FELISA):} + + \title{Unstructured Inviscid\\ Hypersonic Flow Solver\\ (FELISA\_HYP)} + \leftmargin 3in + \begin{items} + \item Euler equations + \item Finite volume formulation + \item Edge data structure + \item H\"{a}nel flux vector splitting + \item MUSCL reconstruction + \item Explicit time stepping + \end{items} +\end{slide} + +\begin{note} + \title{Time Stepping} + \leftmargin 2.5in + \begin{items} + \item check to ensure monotonicity + \item eliminate limit cycle behavior + \end{items} +\end{note} + +\begin{slide}\typeout{Edge Data Structure:} + \title{Edge Data Structure} + \begin{center} + \begin{minipage}{.45\linewidth} + \incfig[\linewidth]{smpfig} + \end{minipage} + \hspace{0.05\linewidth} + \begin{minipage}{.45\linewidth} + \begin{items} + \item control volumes are tetrahedra surrounding each node + \item fluxes computed across outer faces of control volume + \item flux computations grouped by edge + \end{items} + \end{minipage} + \end{center} +\end{slide} + +\begin{note} + \title{Old Edge Data Structure notes\ldots} + \leftmargin 2in + \begin{items} + \item edge il is used in all of the figures\ldots\ + \end{items} + \leftmargin 0in + \begin{tabular}{p{.45\linewidth}p{.45\linewidth}} + \begin{items} + \item fluxes computed across faces of tetrahedra + \item control volume is tetrahedra + \item nodal info for cells is stored + \end{items}& + \begin{items} + \item fluxes computed across $S^e$ for all edges of node~$i$ + \item control volume surrounds node + \item weights for $S^e$ stored + \end{items} + \end{tabular} +\end{note} + +\begin{slide} + \typeout{Flux vector splitting:} + \title{H\"anel Flux Vector Splitting} + \begin{items} + \item Upwind formulation; allows for stable computations + across strong shocks + \item No 'free' parameters are required + \item Allows for constant enthalpy solution where solution is + fully converged + \end{items} +\end{slide} + +\begin{slide}\typeout{Reconstruction:} + \title{Gradient Reconstruction} + \incfig[.8\linewidth]{smpfig} +\end{slide} + +\begin{note} + \title{Gradient Reconstruction notes} + \begin{items} + \item compare to structured grid gradient calculation\\ + \item edge il is used in all of the figures...\\ + \item MUSCL reconstruction + (Monotone Upwind Scheme Conservation Law) + \end{items} +\end{note} + +\begin{slide}\typeout{NASA's use of FELISA:} + \title{Recent Applications of the FELISA System} + \leftmargin 1in + \begin{items} + \item Lockheed-Martin RLV/X-33 Phase I; aerodynamics + \item Lockheed-Martin RLV/X-33 Phase II; + Ascent shock interaction study; transonic aerodynamic screening + \item McDonnell Douglas Phase I RLV/X-33; + control surface loading (NASA CR 201606) + and aerodynamics\\ + (subsonic $\Rightarrow$ hypersonic) + \item OSC X-34, transonic screening, control surface loading + \end{items} +\end{slide} + +\begin{slide}\typeout{X-33 body:} + \title{Code to Code Comparisons for\\ + Preliminary Lockheed--Martin X-33 Vehicle} + \begin{items} + \item Codes:\\ + -- FELISA\_HYP: inviscid, unstructured mesh\\ + -- LAURA: viscous, structured grid\\ + -- DPLUR: inviscid, structured grid, parallel + \item Flow feature, surface pressure comparisons:\\ + -- $M_\infty = 9.8$, $\alpha = 40^{\circ}$ + \item Aerodynamic force and moment comparisons:\\ + -- $M_\infty = 4.5$, experimental data from LaRC UPWT + \end{items} +\end{slide} + +\begin{slide} + \title{X33 Configuration} + \begin{center} + \begin{tabular}{cc} + \incfig[.45\linewidth]{smpfig}& + \incfig[.45\linewidth]{smpfig} + \end{tabular} + \end{center} +\end{slide} + +\begin{note} + \title{Code to Code Comparisons for + Preliminary Lockheed--Martin X-33 Vehicle} + \leftmargin 3in + \begin{items} + \item mention code authors + \end{items} +\end{note} + +\begin{slide}\typeout{How has FELISAHYP been used?} + \title{Grid Generation Time Comparisons} + \begin{items} + \item Initial geometry definition, surface and volume mesh generation + for an X-33 configuration, first~time~$\|$ most~recent: + \begin{items} + \item FELISA: 1.5 weeks $\|$ 4 days + \item structured: 6 weeks $\|$ 3.5 weeks + \end{items} + \item Case-specific grid generation: + bow shock spacing: time consuming for FELISA, 1-2 days + control surface deflections: + \begin{items} + \item $1/2$ day for unstructured + \item $1/2$ week for LAURA + \end{items} + \end{items} +\end{slide} + +\begin{note} + \title{Grid Generation Time Comparisons} + \begin{describe}[.9in] + \item[felisa] put together surfaces, intersection curves, topology + \item[laura] build surface on cad + \end{describe} +\end{note} + +\begin{slide}\typeout{Concluding Remarks:} + \title{Concluding Remarks} + \begin{items} + \item FELISA\_HYP flow solver developed\\ + \item Applied FELISA System with FELISA\_HYP to complex \\configurations + \begin{items} + \item Comparable accuracy to structured grid solvers + \item Faster turn--around time than structured grid methods + \end{items} + \item Significant impact on major NASA programs + \end{items} +\end{slide} + +\end{document} |