NOZZLE MATERIALS
Analytical Comparisons Of Ablative Nozzle Materials
This program is designed to analytically predict the ablation performance of rocket nozzle heat protection materials. The program is based on the use of nonsymmetrical difference equations that are employed to solve systems of complex partial differential equations. The program can be used to predict the thermal degradation of a wide variety of materials exposed to an external source of heat. The program also includes the effects of mass addition on heat transfer, the calculation of internal gas pressure and internal material stresses, and a number of other options for surface or char removal.
Program Size: 7,360 Statements
Computer Language: FORTRAN IV
Copyright (c) 1996 Pacific HiTech, Inc. and COSMIC 
