Accession Number:

ADA256724

Title:

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

Descriptive Note:

Master's thesis

Corporate Author:

NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s):

Report Date:

1992-03-01

Pagination or Media Count:

136.0

Abstract:

Two-dimensional experimental and numerical simulations of a transonic fan blade passage M1.4 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.

Subject Categories:

  • Fluid Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE