Accession Number : ADP007962
Title : Reacting Shock Waves in Hypersonic Propulsion Applications,
Corporate Author : ROME UNIV (ITALY)
Personal Author(s) : Onofri, M.
Report Date : DEC 1990
Pagination or Media Count : 10
Abstract : Problems connected to the occurrence of finite rate chemical processes behind shock waves in hypersonic flowfields are analyzed and a numerical technique is proposed for their solution. The computational difficulties connected with the presence of large gradients of the species concentrations are considered. A method is proposed, based on a shockfitting technique for the gasdynamic model and a variable step integration along the streamlines for the energy and species conservation equations. This approach provides the needed resolution where it is actually required, without becoming cumbersome elsewhere, and the relaxation layer behind shocks can be computed efficiently and precisely.
Descriptors : *SHOCK WAVES, *AIR BREATHING ENGINES, *FLOW FIELDS, *JET PROPULSION, *HYPERSONIC FLOW, APPROACH, CHEMICALS, CONSERVATION, ENERGY, EQUATIONS, GRADIENTS, INTEGRATION, LAYERS, MODELS, RATES, RELAXATION, RESOLUTION, SHOCK, VARIABLES.
Subject Categories : Fluid Mechanics
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE