Iterative calculations for solid rocket ramjet performances on design condition

Thermodynamic parameters calculations are one of the important parts for solid rocket ramjet(SRR) performance analysis. Commonly, the parameters are obtained by means of interpolation from data tables which is established for specified propellant. NASA CEA program is secondary-developed successfully to a subroutine. Based on the afterburner thermodynamic calculations, the iterative algorithm for solid rocket ramjet performance on design point is investigated. The propellant composition, air inlet total pressure recovery coefficient, combustion efficiency, and nozzle impulse efficiency are assumed according to experiment. The iterative algorithm is an utility software for SRR scheme design.