Finite Element Program for Calculating Flows in Turbomachines with Results for NASA Task-1 Compressor.

Abstract

A general mesh generation code (MESHGEN) and finite element flow solver (TURBO) for calculating the flow development through axial turbomachines are fully documented. The finite element approach followed Hirsch and Warzee. Excellent results were obtained for the NASA Task-1 compressor operating with subsonic flow conditions. Construction of the code will allow straightforward extension to transonic flows, turbine stages and multiple stage machines. (Author)

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1982
Accession Number
ADA124987

Entities

People

  • Julian A. Ferguson Iii

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms
  • C4I

DTIC Thesaurus Topics

  • Axial Flow
  • Boundary Layer
  • Compressors
  • Computational Fluid Dynamics
  • Computational Science
  • Computer Programs
  • Finite Element Analysis
  • Flow
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Mathematical Models
  • Plastic Explosives
  • Subsonic Flow
  • Thermodynamic Properties
  • Transonic Flow
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Software Engineering