Control of shock-wave boundary-layer interactions by bleed in supersonic mixed compression inletsAn experimental investigation has been conducted to determine the effect of bleed region geometry and bleed rate on shock wave-boundary layer interactions in an axisymmetric, mixed-compression inlet at a Mach number of 2.5. The full realizable reduction in transformed form factor is obtained by bleeding off about half the incident boundary layer mass flow. Bleeding upstream or downstream of the shock-induced pressure rise is preferable to bleeding across the shock-induced pressure rise. Slanted holes are more effective than normal holes. Two different bleed hole sizes were tested without detectable difference in performance.
Document ID
19750061541
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Fukuda, M. K.
Reshotko, E. (Case-Western-Reserve University Cleveland, Ohio, United States)
Hingst, W. R. (NASA Lewis Research Center Cleveland, Ohio, United States)