Static Pressure Measurements of the Shock-Boundary Layer Interaction in a Simulated Fan Passage

Abstract

Two-dimensional experimental and numerical simulations of a transonic fan blade passage (M=1.4) were conducted to provide baseline data for the study of the effects of vortex generating devices on shock-boundary layer interaction. A back pressure valve was designed for a transonic cascade blowdown wind tunnel, the test section was instrumented, and time-averaged static pressure distributions across the shock-boundary layer interaction were obtained. A numerical Navier-Stokes solution to the flow was also found. Sensitive and repeatable control of the cascade pressure ratio was demonstrated and the flow was shown to be reasonably two-dimensional across the span. Shock-Boundary Layer Interaction, Transonic Cascade Wind Tunnel, Variable Cascade Back Pressure, Boundary Layer Separation.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1992
Accession Number
ADA256724

Entities

People

  • William L. Golden Jr.

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • C4I
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Acquisition
  • Boundary Layer
  • Computational Fluid Dynamics
  • Control Panels
  • Data Acquisition
  • Fluid Dynamics
  • Fluid Flow
  • Leading Edges
  • Measurement
  • Operating Systems
  • Pressure Distribution
  • Pressure Measurement
  • Test Facilities
  • Three Dimensional
  • Turbulent Mixing
  • Two Dimensional
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Fluid Dynamics.