Accession Number : AD0648356

Title :   CALCULATION OF PROPELLANT PERFORMANCE.

Descriptive Note : APL library bulletin translations series,

Corporate Author : JOHNS HOPKINS UNIV SILVER SPRING MD APPLIED PHYSICS LAB

Personal Author(s) : Crampel,Bernard

Report Date : 19 JAN 1967

Pagination or Media Count : 46

Abstract : The article describes the method used by ONERA for calculating the theoretical performance of propellants; it was tested on a large number of propellants. The method was programmed on FORTRAN II for an IBM 704 computer and allows the processing of data relating to substances containing a maximum of 20 elements and capable of giving a total of 250 chemical species in gaseous phase and 20 condensed phases as combustion products. Study of the flow of a gas-particle mixture, with possible changes of the composition in the nozzle, was simplified by assuming that the gaseous phase, which can be considered similar to a theoretically ideal gas, is in thermal and kinetic equilibrium with the condensed particles, the volume of which is negligible as compared with the specific volume of the gas. Once the pressure and temperature have been determined, calculation of the composition in the equilibrium state by the Brinkley method makes it possible to define with these assumptions the thermodynamic state of the system: enthalpy, entropy, specific heat, isentropic expansion coefficient, and sound velocity. General classical equations, applied to a one-dimensional isentropic flow, then permit determination of the state of the system in each section of the nozzle and calculation of the main thrust-related parameters characteristic of rocket engines. (Author)

Descriptors :   (*ROCKET PROPELLANTS, PERFORMANCE(ENGINEERING)), COMPUTER PROGRAMS, THRUST, FLUID MECHANICS, TWO PHASE FLOW, THERMODYNAMICS, CHEMICAL EQUILIBRIUM, CHEMICAL ELEMENTS, ROCKET NOZZLES, FRANCE

Subject Categories : Rocket Propellants

Distribution Statement : APPROVED FOR PUBLIC RELEASE