Documentation of Cascade Unsteady Pressure Difference Program.

Abstract

The response of an axial-flow turbomachine to spatial velocity variations can be determined by the unsteady pressure distribution function which has been developed and represents an extension of an earlier analysis of the unsteady lift. A computer program has been written to formulate the unsteady pressure difference as a function of design parameters. This program is versatile in that it includes the effects of the cascade geometrical parameters and disturbance flow characterisitics, such as the blade camber, angle of incidence, nonconvected disturbance, and it also gives the unsteady lift and moment. The documentation and the use of this program are presented herein. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jan 05, 1980
Accession Number
ADA083987

Entities

People

  • I-c. Shen

Organizations

  • Pennsylvania State University

Tags

Communities of Interest

  • Air Platforms
  • C4I

DTIC Thesaurus Topics

  • Angle Of Incidence
  • Axial Flow
  • Bessel Functions
  • Coefficients
  • Computer Programs
  • Computers
  • Coordinate Systems
  • Flow
  • Flow Fields
  • Frequency
  • Geometry
  • Navy
  • Pressure Distribution
  • Procedures (Computers)
  • Test And Evaluation
  • Two Dimensional
  • Universities

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Theoretical Analysis.