Computational Analysis of a Single-Element, Shear-Coaxial, GH2/GO2 Engine

Abstract

As part of a program to develop a computational methodology to obtain high-fidelity rocket engine flow solutions, computations were performed on a single element, gas/gas, H2/O2 combustion engine. The solutions are compared with previously reported solutions to this problem, showing that the problem can be solved on a finer grid with a second-order accurate scheme, thus providing another level of detail to the flow physics. Additional time-accurate solutions are also presented. Comparisons among a "quasi-steady" solution, averaged time-accurate solution, and experimental data are made and shown that for inherently unsteady flows, a time-accurate solution does as well as or better than a steady solution.

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Document Details

Document Type
Technical Report
Publication Date
Oct 03, 2001
Accession Number
ADA410952

Entities

People

  • Douglas G. Talley
  • Mark Archambault
  • Oshin Peroomian

Organizations

  • Air Force Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force Research Laboratories
  • Boundary Layer
  • Combustion
  • Combustion Products
  • Computational Fluid Dynamics
  • Computations
  • Engines
  • Equations
  • Experimental Data
  • Flow
  • Fluid Flow
  • Heat Transfer
  • Large Eddy Simulation
  • Layers
  • Mechanical Engineering
  • Turbulent Mixing
  • Unsteady Flow

Fields of Study

  • Physics

Readers

  • Calculus or Mathematical Analysis
  • Computational Fluid Dynamics (CFD)