Transonic Fan/Compressor Rotor Design Study. Volume 4

Abstract

Volumes I through VI of this report describes the aerodynamic design of a series of five transonic rotors all parametrically related to a baseline design documented in Technical Report AFAPL-TR-79-2078. Each of the five designs deviate from the base line, in so far as practical, by a variation of one parameter only. The parametric variations are specified at the rotor tip. This volume describes the aerodynamic design details of the Phase III rotor. The Phase III rotor was designed to have a steeper average suction surface angle in the supersonic region ahead of the shock than the baseline rotor. This results in a smaller cascade throat area in the outer 80% of the blade than the baseline rotor. The hub region was kept essentially the same as the baseline rotor.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1982
Accession Number
ADB069404

Entities

People

  • D. E. Parker
  • M. R. Simonson

Organizations

  • General Electric

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Air Force
  • Air Force Facilities
  • Aircraft Engines
  • Base Lines
  • Commerce
  • Compressors
  • Computer Programs
  • Flow
  • Governments
  • Leading Edges
  • Mach Number
  • Pressure Distribution
  • Static Pressure
  • Test And Evaluation
  • United States Government
  • Virtual Reality

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering
  • Business Analytics

Technology Areas

  • Hypersonics