
Accession Number : AD0676671
Title : APPLICATION OF THE METHOD OF PARAMETRIC DIFFERENTIATION TO RADIATION GASDYNAMICS.
Descriptive Note : Technical rept.,
Corporate Author : MASSACHUSETTS INST OF TECH CAMBRIDGE AEROPHYSICS LAB
Personal Author(s) : Jischke,Martin C.
Report Date : JUL 1968
Pagination or Media Count : 298
Abstract : It is shown that the method of parametric differentiation, used in solving nonlinear systems of equations, can be interpreted as a device for introducing a real 'parameter' characteristic into the mathematical description of the problem along which one can integrate the parametrically differentiated system of equations. In this way, the method of parametric differentiation yields a characteristic initial value problem where the necessary data along distinct families of characteristics are the parametrically differentiated boundary conditions of the original problem and a solution of the original system for a particular value of the descriptive parameter. The applicability of the method of parametric differentiation to problems in radiation gasdynamics is first indicated by the solution of a simple test problem  the onedimensional, hypersonic, radiating shock layer. Treating the total optical depth of the shock layer as the descriptive parameter, solutions were obtained for a large range of values of this parameter which appeared to be consistent with existing approximate solutions. The utility of this technique in radiation gasdynamics is further demonstrated in a solution of the problem of an inviscid, radiating gas flow in the stagnation region of a blunt body. (Author)
Descriptors : (*BOUNDARY VALUE PROBLEMS, *NONLINEAR DIFFERENTIAL EQUATIONS), (*REENTRY VEHICLES, AERODYNAMIC HEATING), (*ATMOSPHERE ENTRY, HYPERSONIC CHARACTERISTICS), PROBLEM SOLVING, HEAT TRANSFER, BOUNDARY VALUE PROBLEMS, BLUNT BODIES, SHOCK WAVES, STAGNATION POINT, THERMAL RADIATION, ONE DIMENSIONAL FLOW, PERTURBATION THEORY, COMPUTER PROGRAMS, DIFFERENCE EQUATIONS
Subject Categories : Numerical Mathematics
Guided Missiles
Fluid Mechanics
Thermodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE