Accession Number : AD0744858
Title : Optimum Radiative Transfer Geometries in Hypersonic Flow.
Descriptive Note : Technical rept.,
Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE AEROPHYSICS LAB
Personal Author(s) : Gibeling,Howard J.
Report Date : JUN 1972
Pagination or Media Count : 261
Abstract : The methods of optimal control theory have been applied to achieve minimization of radiative energy transfer to a two-dimensional body of finite length. Molecular transport properties and real gas effects have been excluded, and local thermodynamic equilibrium as well as a gray gas was assumed. The radiation field was specified by the differential approximation. The main emphasis was on the effect of changes in body geometry on the radiative energy transfer to the surface. Only attached shock waves were considered. The coupled flow and radiation fields were determined based upon a one-strip integral method. Optimal solutions have been obtained for a sequence of nose angles. (Author)
Descriptors : (*REENTRY VEHICLES, AERODYNAMIC HEATING), HEAT TRANSFER, ENERGY, THERMAL RADIATION, HYPERSONIC CHARACTERISTICS, COOLING, CONTROL, THEORY, MATHEMATICAL MODELS, SHOCK WAVES, NOSE CONES, AERODYNAMIC CONFIGURATIONS
Subject Categories : Guided Missile Reentry Vehicles
Distribution Statement : APPROVED FOR PUBLIC RELEASE