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.