Aerodynamic computer code for analyzing heat transfer and pressure loads on missiles

An aerodynamic computer code was developed for calculating the pressure distribution on a missile or its components, e.g., body and wings and subsequently interpolating the results by surface fit at locations as specified for structural analysis using the NASTRAN computer code. The code is valid from subsonic up to high supersonic speeds and for generalized attitudes of the missile. Subroutines have been added to the code to enable calculation of temperature histories, equilibrium temperature and heat flux at arbitrary locations on a missile. In addition, capability for treating slightly blunted nose configurations has been incorporated.