Application of Astrium's CryoROC Code to a Single Injector Problem. A Contribution to the RCM-3 Mascotte Test Case (60 bar)

Abstract

This paper presents a numerical analysis of the RCM-3 Mascotte test case (60 bar) with CryoROC, Astrium's advanced multiphase Navier-Stokes solver. The CryoROC spray combustion CFD-code was developed and intended to simulate the flowfield and the heat exchange within existing and future cryogenic rocket thrust chambers. For that purpose, the computational approach so far excluded too much effort on precise modelling the vicinity of the injector head with its single elements. It's rather a question of whether the code's predictions are efficient, fast and precise enough regarding the whole thrust chamber and its global characteristics. The CryoROC code is an important tool used in the thrust chamber layout process at Astrium.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 2001
Accession Number
ADP012371

Entities

People

  • Josef Gorgen
  • Oliver Knab

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Atomization
  • Boltzmann Equation
  • Boundaries
  • Boundary Layer
  • Chambers
  • Chemical Reactions
  • Combustion
  • Computational Fluid Dynamics
  • Computational Science
  • Computations
  • Equations
  • Heat Transfer
  • Near Field
  • Numerical Analysis
  • Rockets
  • Standards
  • Thrust Chambers

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Computational Fluid Dynamics (CFD)
  • Computer Engineering