Static pressure measurements of the shock-boundary layer interaction in a simulated fan passage
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Authors
Golden, William L.
Subjects
Shock-Boundary Layer Interaction
Transonic Cascade Wind Tunnel
Variable Cascade Back. Pressure
Boundary Layer Separation
Transonic Cascade Wind Tunnel
Variable Cascade Back. Pressure
Boundary Layer Separation
Advisors
Shreeve, Raymond P.
Date of Issue
1992-03
Date
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
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 shockboundary
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.
Type
Thesis
Description
Series/Report No
Department
Astronautical Engineering
Organization
Naval Postgraduate School
Identifiers
NPS Report Number
Sponsors
Funder
Format
123 p.;28 cm.
Citation
Distribution Statement
Approved for public release; distribution is unlimited.