Analysis of Unsteady Aerodynamic Effects on an Axial-Flow Compressor Stage with Distorted Inflow

Abstract

An analytical procedure has been developed to predict the circumferential pressure profile at the exit of a compressor stage subjected to a spatially steady inlet distortion. Expressions have been developed relating the pressure ratio and weight flow characteristics of an axial-flow compressor stage to the normal force and drag characteristics of an isolated airfoil. These steady-state interrelations between rotor and isolated airfoil were used to apply available unsteady data for isolated airfoils in the study of distorted inflow effects. Both unsteady and quasi-steady predictions were made and were compared with available experimental results from low-speed compressor tests.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1972
Accession Number
AD0746457

Entities

People

  • Franklin O. Carta

Organizations

  • Purdue University

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Axial Flow
  • Axial Flow Compressors
  • Boundary Layer
  • Computational Fluid Dynamics
  • Equations
  • Experimental Data
  • Fluid Dynamics
  • Fluid Flow
  • Plastic Explosives
  • Potential Flow
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Static Pressure
  • Steady Flow
  • Steady State

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Theoretical Analysis.