The Effects of Active Cooling on the Aerodynamic and Aerothermodynamic Characteristics of Slender Bodies of Revolution
Report Number: AFFDL TR 64-187
Author(s): Leadon, B. M., Rosciszeski, Jan., Gallaher, W. H., Holst, W. R., Carter, W. V.
Corporate Author(s): General Dynamics/Convair
Laboratory: AF Flight Dynamics Laboratory
Date of Publication: 1964-12
Pages: 106
Contract: AF 33(657)-11679
DoD Project: 1366
DoD Task: 136607
Identifier: AD0615471
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.
Provenance: Lockheed Martin Missiles & Fire Control
Author(s): Leadon, B. M., Rosciszeski, Jan., Gallaher, W. H., Holst, W. R., Carter, W. V.
Corporate Author(s): General Dynamics/Convair
Laboratory: AF Flight Dynamics Laboratory
Date of Publication: 1964-12
Pages: 106
Contract: AF 33(657)-11679
DoD Project: 1366
DoD Task: 136607
Identifier: AD0615471
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.
Provenance: Lockheed Martin Missiles & Fire Control