[PDF] Numerial Investigation Of Twin Nozzle Rocket Plume Phenomenology eBook

Author : Houshang Ebrahimi
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Page : 13 pages
File Size : 19,47 MB
Release : 1997
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The Generalized Implicit Flow Solver (GIES) computer program, developed under sponsorship of the Air Force Phillips Laboratory, Edwards Air Force Base, CA, has been modified and used for three-dimensional reacting two-phase flow problems. The intent of the original GIFS development effort was to provide the JANNAF community with a standard computational methodology to simulate multiple nozzle/plume flow-field phenomena and other three-dimensional effects. Recent development efforts have concentrated on improving the run time and robustness of the algorithm. The GIFS computer program was originally released as an untested research version. Since that time, several corrections and enhancements have been made to the model. The Van Leer Flux Splitting option has been successfully implemented into the existing GIFS model and provides a more robust solution scheme. A Parabolized Navier-Stokes (PNS) version of the GIFS algorithm is currently under development and is intended to substantially improve the run-time requirements for flow fields dominated by supersonic flow regimes. These improvements and enhancements will foster the application of the GIFS model in the CFD community. This paper reports the significant results of several twin-nozzle/plume applications of the GIFS code. Six simulations of Titan II plume flow fields have been completed to assess the effects of three-dimensionality, turbulent viscosity, afterburning, near-field shock structure, finite-rate kinetic chemistry, intranozzle geometric spacing, and initial nozzle exit plane profile effects on the subsequent plume exhaust flow field. The results of these calculations indicate that the viscous stress model, kinetic chemistry, and nozzle exit profile are significant parameters that should be considered in analyses and interpretation of the calculations.

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Page : 13 pages
File Size : 20,40 MB
Release : 1998
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The Generalized Implicit Flow Solver (GIFS) computer program has been modified and applied for analysis of three-dimensional, reacting, two-phase flow simulation problems. The intent of the original GIFS development effort was to provide the Joint Army, Navy, NASA, Air Force (JANNAF) community with a standard computational methodology to simulate multiple nozzle/plume flow-field phenomena and other three-dimensional effects. The Van Leer Flux Splitting option has been successfully implemented into the existing GIFS model and provides a more robust solution scheme, making application of the model more reasonable for engineering applications. This paper is a continuation of the previous work and reports the significant results of parametric flow-field simulations resulting from a dual-nozzle propulsion system operating at a high-altitude flight condition. In support of this effort, four calculations of Titan II SLV flow fields have been completed to assess the effects of three-dimensionality, missile body effects, chemistry, and gas generator flow on simulated plume exhaust flow-field properties. These calculations indicate that three-dimensionality is always an important factor and could substantially influence the interpretation of the results. If three dimensional effects are oversimplified in the model, analyses of the spatial results can be misinterpreted and misapplied. The missile body effect can also generate three-dimensional influences affecting the Mach reflection location, the plume/plume impingement shock location, inviscid shock structure, and shear layer growth. The gas generator flow influences the very near field simulation but is significantly dampened beyond approximately 1 meter downstream of the nozzle exit (nonreacting). If missile base heating, recirculation effects, or nozzle impingement heat-transfer analyses are required, the gas generator flow, including a kinetic chemistry model is the dominant influence.