A Computer Code for Fully-Coupled Rocket Nozzle Flows (FULLNOZ).

摘要

A comprehensive computer code (FULLNOZ) has been developed to perform detailed calculations of rocket nozzle flows downstream of the sonic line. The code uses the streamtube method to integrate the hyperbolic governing equations of steady supersonic flow. The program represents a significant advance in nozzle flow predictions through the coupling of gas/particle nonequilibrium effects, nonequilibrium chemistry, turbulent boundary layers (to determine the effects of wall heat transfer and shear stress) and turbulent mixing across streamtubes. This report describes the analytical and numerical techniques employed by the code, presents results of a sample calculation for the Minuteman Stage 2 nozzle and gives complete instructions on the preparation of input data and a full FORTRAN listing.