Accession Number:

ADA058869

Title:

Computer Programs to Calculate Chemically Reacting Flow in Axisymmetric Nozzles.

Descriptive Note:

Technical rept.,

Corporate Author:

PROPELLANTS EXPLOSIVES AND ROCKET MOTOR ESTABLISHMENT WESTCOTT (ENGLAND)

Personal Author(s):

Report Date:

1978-05-01

Pagination or Media Count:

51.0

Abstract:

This report describes a set of computer programs which calculates the inviscid two-dimensional expansion of gaseous exhaust mixtures through rocket nozzles. Equilibrium chemistry in the combustion chamber and as far as the nozzle throat is assumed, whilst finite rate or frozen chemistry may be applied from the throat onwards. The transonic flow field is calculated by the method of streamline curvature and the flow in the supersonic region of the nozzle is solved by the method of characteristics. The theory on which the programs are based is summarised and a comprehensive users guide is included. A sample calculation is presented. Author

Subject Categories:

  • Computer Programming and Software
  • Fluid Mechanics
  • Combustion and Ignition

Distribution Statement:

APPROVED FOR PUBLIC RELEASE