Investigation of a Mach 1.4 Compressor Cascade with Variable Back Pressure Using Flow Visualization.

Abstract

Flow through a transonic compressor cascade model was investigated at M = 1.4 using flow visualization and pressure measurements. Shock patterns for two different blade incidences were documented at increasing back pressures. Data were taken up to a maximum pressure ratio of 1.53 at estimated minimum loss incidence conditions. An oblique shock system persisted, producing large flow turning (6.8 deg) and a slightly supersonic exit mach number (1.02). Losses and blade pressure loading were calculated using a combination of test data and computational approximations. Failure of blade retaining tabs occurred with both aluminum and steel cascade blades. Failures were attributed to fatigue from high oscillatory stress levels and redesigned blade mounts were proposed. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1986
Accession Number
ADA168647

Entities

People

  • Michael G. Hegland

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms
  • C4I
  • Sensors
  • Space

DTIC Thesaurus Topics

  • Boundary Layer
  • Cameras
  • Compressors
  • Computational Fluid Dynamics
  • Detectors
  • Flow Visualization
  • Fluid Flow
  • Geometry
  • Hypervelocity Flow
  • Mach Number
  • Mass Flow
  • Measurement
  • Mechanical Properties
  • Photographs
  • Pressure Distribution
  • Pressure Measurement
  • Static Pressure

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Mathematics or Statistics
  • Mechanical Engineering/Mechanics of Materials.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow