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Flow unsteadiness effects on boundary layersThe development of boundary layers at high subsonic speeds in the presence of either mass flux fluctuations or acoustic disturbances (the two most important parameters in the unsteadiness environment affecting the aerodynamics of a flight vehicle) was investigated. A high quality database for generating detailed information concerning free-stream flow unsteadiness effects on boundary layer growth and transition in high subsonic and transonic speeds is described. The database will be generated with a two-pronged approach: (1) from a detailed review of existing literature on research and wind tunnel calibration database, and (2) from detailed tests in the Boundary Layer Apparatus for Subsonic and Transonic flow Affected by Noise Environment (BLASTANE). Special instrumentation, including hot wire anemometry, the buried wire gage technique, and laser velocimetry were used to obtain skin friction and turbulent shear stress data along the entire boundary layer for various free stream noise levels, turbulence content, and pressure gradients. This database will be useful for improving the correction methodology of applying wind tunnel test data to flight predictions and will be helpful for making improvements in turbulence modeling laws.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Murthy, Sreedhara V.
(University of the Pacific Stockton, CA, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1989
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NAS 1.26:186067
Accession Number
Funding Number(s)
Distribution Limits
Work of the US Gov. Public Use Permitted.
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