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Measuremants in the wake of an infinite swept airfoilThis is a report of the measurements in the trailing edge region as well as in the report of the developing wake behind a swept NACA 0012 airfoil at zero incidence and a sweep angle of 30 degrees. The measurements include both the mean and turbulent flow properties. The mean flow velocities, flow inclination and static pressure are measured using a calibrated three-hole yaw probe. The measurements of all the relevant Reynolds stress components in the wake are made using a tri-axial hot-wire probe and a digital data processing technique developed by the authors. The development of the three dimensional near-wake into a nearly two dimensional far-wake is discussed in the light of the experimental data. A complete set of wake data along with the data on the initial boundary layer in the trailing edge region of the airfoil are tabulated in an appendix to the report.
Document ID
19830002816
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Novak, C. J. (Iowa Univ. Iowa City, IA, United States)
Ramaprian, B. R. (Iowa Univ. Iowa City, IA, United States)
Date Acquired
September 4, 2013
Publication Date
April 1, 1982
Subject Category
Aerodynamics
Report/Patent Number
IIHR-240
NASA-CR-169464
PB82-212499
NAS 1.26:169464
Accession Number
83N11086
Funding Number(s)
CONTRACT_GRANT: NAG2-110
CONTRACT_GRANT: NSG-1200
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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