A computer code (SKINTEMP) for predicting transient missile and aircraft heat transfer characteristics

Abstract

A FORTRAN computer code (SKlNTEMP) has been developed to calculate transient missile/aircraft aerodynamic heating parametcrs utilizing basic flight parameters such a<; altitude, Mach number, and angle of attack. The insulated skin temperature of a vehicle surface on either the fuselage (axisymmetric body) or wing (two-dimensional body) is computed from a basic heat balance relationship throughout the enlire spectrum (subsonic, transonic, supersonic, hypersonic) of flight. This calculation method employs a simple finite diffcrenee procedure which considers radiation, forced convection, and non-reactive chemistry. Surface pressure estimates arc ba<>ed on a modified Newtonian flow model. Eckert's reference temperature method is used as the forced convection heat transfer model. SKlNTEMP predictions are compared with a limited number of test cases. SKlNTEMP was developed as a tool to enhance the conceptual design process of high speed missiles and aircraft. Recommendations are made for possible future development of SKINTEMP to further support the design process.