A Fully-Coupled Underexpanded Afterburning Rocket Plume Program (the AIPP Code). Part II. Program User's Manual.
Final rept. 1 Oct 72-31 Jul 75,
AEROCHEM RESEARCH LABS INC PRINCETON N J
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A comprehensive computer code has been developed to determine afterburning rocket plume characteristics over a wide altitude range. The code constitutes a significant advance over previous plume codes because it computes the plume shock structure while simultaneously accounting for turbulent mixing, nonequilibrium chemistry and gasparticle nonequilibrium effects. The capability of calculating properties in the matched subsonicsupersonic region downstream of the Mach disc and in the far field has been incorporated into the code. Some of the more important limitations of the code are the vehicle velocity must be supersonic the missile base recirculation region is negligibly small the axial location of the Mach disc is determined from existing correlations of experimental data and internal plume shocks are not considered downstream of the Mach disc. This report is the program users manual for the AIPP code and includes instructions for preparation of input data, a description of all subroutines, a program flow chart, sample output and a FORTRAN listing. Author
- Computer Programming and Software
- Fluid Mechanics
- Rocket Engines