Accession Number:

ADA038151

Title:

Two-Dimensional, Two-Phase Flow Through a Rocket Exhaust Nozzle: A Progress Report,

Descriptive Note:

Corporate Author:

ROCKET PROPULSION ESTABLISHMENT WESTCOTT (ENGLAND)

Personal Author(s):

Report Date:

1976-08-01

Pagination or Media Count:

32.0

Abstract:

This memorandum describes progress in the development of a set of computer programs which solve the equations of gasparticle flow throgh an axisymmetric nozzle. Tow programs have been writtern to solve the equations in the transonic throat region of the nozzle. The first treats the two-phase fluid as a heavy perfect gas with modified isentropic exponent and molecular weight, and solves the equations of isentropic transonic flow. An initial flow field configuration is obtained for input to the second program, which incorporates non-equilibrium effects of the gasparticle mixture. The programs provide accurate initial line data for starting a supersonic calculation, and will be used as input to a third program, soon to be written, for solving the two-phase flow equations in the supersonic region of the nozzle. Author

Subject Categories:

  • Fluid Mechanics
  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE