Accession Number : AD0429198

Title :   ABLATING BODY HEAT TRANSFER,

Corporate Author : AEROSPACE CORP EL SEGUNDO CALIF

Personal Author(s) : Quinville,J. A. ; Solomon,J.

Report Date : 15 JAN 1964

Pagination or Media Count : 84

Abstract : A computational technique is described that determines the transient aerodynamic heating and ablation of a vehicle throughout an arbitrary flight trajectory. Both laminar and turbulent boundary layers are treated for flows over blunt or sharp nosed two-dimensional or axisymmetric bodies. The effects of real gas dissociation as well as chemically reacting ablation are considered. The chemical reactions include both diffusion limited and rate limited combustion of carbon. The transient heat conduction model treats the one-dimensional flow of heat into a material which may be of the char-forming type with internal depolymerization. The computational technique has been coded in Fortran for an IBM 7090. The numerical solutions for an ablating char forming material using the complete boundary layer and heat conduction programs are considered satisfactory. However, the IBM 7090 execution time was longer than desired. The combined programs can be improved from the present conditions in several areas leading to shorter computational times. (Author)

Descriptors :   (*REENTRY VEHICLES, AERODYNAMIC HEATING), (*BLUNT BODIES, AERODYNAMIC HEATING), (*CONICAL BODIES, AERODYNAMIC HEATING), HEAT TRANSFER, ABLATION, LAMINAR BOUNDARY LAYER, TURBULENT BOUNDARY LAYER, GAS FLOW, DISSOCIATION, REACTION KINETICS, THERMAL CONDUCTIVITY, PYROLYTIC GRAPHITE, HEAT SHIELDS, CYLINDRICAL BODIES, FLARED AFTERBODIES, FRICTION, PRESSURE, FROZEN EQUILIBRIUM FLOW, MATHEMATICAL ANALYSIS, MATHEMATICAL MODELS, NUMERICAL ANALYSIS, DIGITAL COMPUTERS, NOSE CONES

Distribution Statement : APPROVED FOR PUBLIC RELEASE