439 research outputs found
Study of laser heated propulsion devices. Part 2: Assessment of laser propulsion modeling and simulation requirements
Theoretical models for the laser heated thruster are reviewed. The requirements for an improved laser heated thruster theoretical model are discussed. The application of a time dependent finite difference Navier-Stokes equation solution to the laser heated thruster problem is described, along with a simple closed form solution which was developed in order to gain insight into the difficulties encountered in the pursuit of the numerical solution
Hypersonic flow of air past a circular cylinder with non-equilibrium oxygen dissociation including dissociation of the free stream
Hypersonic inviscid flow past a circular cylinder with nonequilibrium oxygen dissociation and dissociation of the free strea
Duct flow nonuniformities study for space shuttle main engine
To improve the Space Shuttle Main Engine (SSME) design and for future use in the development of generation rocket engines, a combined experimental/analytical study was undertaken with the goals of first, establishing an experimental data base for the flow conditions in the SSME high pressure fuel turbopump (HPFTP) hot gas manifold (HGM) and, second, setting up a computer model of the SSME HGM flow field. Using the test data to verify the computer model it should be possible in the future to computationally scan contemplated advanced design configurations and limit costly testing to the most promising design. The effort of establishing and using the computer model is detailed. The comparison of computational results and experimental data observed clearly demonstrate that computational fluid mechanics (CFD) techniques can be used successfully to predict the gross features of three dimensional fluid flow through configurations as intricate as the SSME turbopump hot gas manifold
Inviscid hypersonic flow of chemically relaxing air about pointed circular cones
Inviscid hypersonic flow of chemically relaxing air about pointed circular cone
Evaluation of absorption cycle for space station environmental control system application Interim report
Zero-gravity absorption refrigeration system design and performance testing for space station environmental control applicatio
Numerical analysis of flow non-uniformity in the hot gas manifold of the Space Shuttle main engine
Three-dimensional viscous flow in a conceptual hot gas manifold (HGM) for the Space Shuttle Main Engine High Pressure Fuel Turbopump (SSME HPFTP) was numerically analyzed. A finite difference scheme was used to solve the Navier-Stokes equations. The exact geometry of the SSME HGM was modeled using boundary fitted curvilinear coordinates and the General Interpolants Method (GIM) code. Slight compressibility of the subsonic flow was modeled using a linearized equation of state with artificial compressibility. A time relaxation method was used to obtain a steady state solution. The feasibility and potential usefulness of computational methods in assisting the design of SSME components which involves the flow of fluids within complex geometrical shapes is demonstrated
Influence of disproportionated rosin acid soap on the emulsion polymerization kinetics of styrene
Development of the general interpolants method for the CYBER 200 series of supercomputers
The General Interpolants Method (GIM) is a 3-D, time-dependent, hybrid procedure for generating numerical analogs of the conservation laws. This study is directed toward the development and application of the GIM computer code for fluid dynamic research applications as implemented for the Cyber 200 series of supercomputers. An elliptic and quasi-parabolic version of the GIM code are discussed. Turbulence models, algebraic and differential equations, were added to the basic viscous code. An equilibrium reacting chemistry model and an implicit finite difference scheme are also included
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