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The Effects of Active Cooling on the Aerodynamic and Aerothermodynamic Characteristics of Slender Bodies of Revolution.

AD615471

Publication Date	1964
Personal Author	Leadon, B. M.; Rosciszewski, J.; Gallaher, W. H.; Holst, W. R.; Carter, W. V.
Page Count	2
Abstract	A new self consistent method has been developed for calculation of boundary layer with mass injection. The system of partial differential equations is reduced to a system of ordinary differential equations by integration over different strips. The velocity and enthalpy profiles are assumed to be expressed by series of error functions. A method of calculating the initial velocity and enthalpy profiles, based on an analysis of singularity, is presented herein. The calculation of the initial profiles is reduced to the solution of a system of transcendential equations. The initial derivatives are calculated from linearlized equations near the singular points and provide a smooth start of integration of the downstream equations. The present method was applied to the cases of a sharp edged body and a blunt body. In addition to the velocity and enthalpy profiles, the pressure distribution and shock layer thickness can be calculated from generalized Newtonian expressions developed as a part of this effort. (Author)
Keywords	AERODYNAMIC CHARACTERISTICS SLENDER BODIES THERMODYNAMICS COOLING BOUNDARY LAYER BLUNT BODIES FLUID FLOW VELOCITY PARTIAL DIFFERENTIAL EQUATIONS DIFFERENTIAL EQUATIONS INTEGRATION NUMERICAL ANALYSIS ENTHALPY EQUATIONS
Corporate Authors	General Dynamics/Convair San Diego Calif
Document Type	Technical Report
Title Note	Final rept.
NTIS Issue Number	196513
Contract Number	AF33 657 11679

The Effects of Active Cooling on the Aerodynamic and Aerothermodynamic Characteristics of Slender Bodies of Revolution.

The Effects of Active Cooling on the Aerodynamic and Aerothermodynamic Characteristics of Slender Bodies of Revolution.
AD615471

Publication Date	1964
Personal Author	Leadon, B. M.; Rosciszewski, J.; Gallaher, W. H.; Holst, W. R.; Carter, W. V.
Page Count	2
Abstract	A new self consistent method has been developed for calculation of boundary layer with mass injection. The system of partial differential equations is reduced to a system of ordinary differential equations by integration over different strips. The velocity and enthalpy profiles are assumed to be expressed by series of error functions. A method of calculating the initial velocity and enthalpy profiles, based on an analysis of singularity, is presented herein. The calculation of the initial profiles is reduced to the solution of a system of transcendential equations. The initial derivatives are calculated from linearlized equations near the singular points and provide a smooth start of integration of the downstream equations. The present method was applied to the cases of a sharp edged body and a blunt body. In addition to the velocity and enthalpy profiles, the pressure distribution and shock layer thickness can be calculated from generalized Newtonian expressions developed as a part of this effort. (Author)
Keywords	AERODYNAMIC CHARACTERISTICS SLENDER BODIES THERMODYNAMICS COOLING BOUNDARY LAYER BLUNT BODIES FLUID FLOW VELOCITY PARTIAL DIFFERENTIAL EQUATIONS DIFFERENTIAL EQUATIONS INTEGRATION NUMERICAL ANALYSIS ENTHALPY EQUATIONS
Corporate Authors	General Dynamics/Convair San Diego Calif
Document Type	Technical Report
Title Note	Final rept.
NTIS Issue Number	196513
Contract Number	AF33 657 11679