Design of Shock-Free Transonic Flow in Turbomachinery.

Abstract

A new design method for transonic flow in turbomachinery is described. The idea is based on the author's previous experience with hodograph methods but carried out in physical space. If combined with a flow analysis code the new method can be used as a design/analysis tool. Results illustrating this procedure are given for two dimensional flow through cascades and past airfoils. Existing configurations can be made shock-free by computational modifications which are limited to that portion of the design shape which is wetted by supersonic flow. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1978
Accession Number
ADA067703

Entities

People

  • Helmut Sobieczky

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Boundary Layer
  • Boundary Value Problems
  • Computational Fluid Dynamics
  • Computational Science
  • Differential Equations
  • Flow Fields
  • Fluid Mechanics
  • Gas Flow
  • Geometry
  • Mach Number
  • Navy
  • Poisson Equation
  • Pressure Distribution
  • Supersonic Flow
  • Transonic Flow
  • Turbomachinery
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Computer Science.
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow
  • Space
  • Space - Hall-Effect Thruster