Topics include: upper stage engine key requirements and design drivers; Calspan "stage 1" results, He slot injection into hypersonic flow (air); test articles for shock generator diagram, slot injector details, and instrumentation positions; test conditions; modeling approach; 2-d grid used for film cooling simulations of test article; heat flux profiles from 2-d flat plate simulations (run #4); heat flux profiles from 2-d backward facing step simulations (run #43); isometric sketch of single coolant nozzle, and x-z grid of half-nozzle domain; comparison of 2-d and 3-d simulations of coolant nozzles (run #45); flowfield properties along coolant nozzle centerline (run #45); comparison of 3-d CFD nozzle flow calculations with experimental data; nozzle exit plane reduced to linear profile for use in 2-d film-cooling simulations (run #45); synthetic Schlieren image of coolant injection region (run #45); axial velocity profiles from 2-d film-cooling simulation (run #45); coolant mass fraction profiles from 2-d film-cooling simulation (run #45); heat flux profiles from 2-d film cooling simulations (run #45); heat flux profiles from 2-d film cooling simulations (runs #47, #45, and #47); 3-d grid used for film cooling simulations of test article; heat flux contours from 3-d film-cooling simulation (run #45); and heat flux profiles from 3-d and 2-d film cooling simulations (runs #44, #46, and #47).

A one-dimensional analytical model of liquid film cooling in rocket engine combustion chambers is developed and compared with existing data. The vapor generated at the liquid interface greatly decreases the convective heat flux and is treated as a 'transition' process. The radiant heat is absorbed at the walls and transmitted to the liquid film by boiling, which can lead to burnout of the film. Downstream of the liquid film, the vapor provides continued thermal protection to the wall and is treated as a gaseous film cooling process. A standard correlation is expressed in differential form to allow for the nonuniform free-stream flow in the nozzle. Liquid film lengths are well predicted by the model. Downstream of the dry-out point, wall temperatures are well predicted up to the start of convergence. Downstream of the converging turn, a correction term, correlated by a centrifugal parameter, is required to account for increased mixing at the converging turn. Downstream of the throat, wall temperatures decrease very quickly because of acceleration of the boundary- layer gases, an effect not included in the model.

This book comprises the proceedings of the 1st International Conference on Fluid, Thermal and Energy Systems. The contents of this book focus on phase change heat transfer, advanced energy systems, separated flows, turbulence and multi-phase modeling, computational fluid flow and heat transfer, thermal energy storage systems, integrated energy systems, nuclear thermal hydraulics, heat transfer in nanofluids, etc. This book serves as a useful reference to researchers, academicians, and students interested in the broad field of thermo-fluid science and engineering.