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An experimental study of the effects of bodyside compression on forward swept sidewall compression inlets ingesting a turbulent boundary layerForward swept sidewall compression inlets have been tested in the Mach 4 Blowdown Facility at the NASA Langley Research Center to study the effects of bodyside compression surfaces on inlet performance in the presence of an incoming turbulent boundary layer. The measurements include mass flow capture and mean surface pressure distributions obtained during simulated combustion pressure increases downstream of the inlet. The kerosene-lampblack surface tracer technique has been used to obtain patterns of the local wall shear stress direction. Inlet performance is evaluated using starting and unstarting characteristics, mass capture, mean surface pressure distributions and permissible back pressure limits. The results indicate that inlet performance can be improved with selected bodyside compression surfaces placed between the inlet sidewalls.
Document ID
19930065518
Document Type
Conference Paper
Authors
Rodi, Patrick E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
July 1, 1993
Subject Category
AERODYNAMICS
Report/Patent Number
AIAA PAPER 93-3125
Meeting Information
AIAA, Fluid Dynamics Conference(Orlando, FL)
Distribution Limits
Public
Copyright
Other