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Direct measurements at Mach 6 of turbulent skin-friction reduction by injection from single and multiple flush slotsThe surface skin-friction reduction downstream of one to four successive flush slots injecting at an angle of 10 deg into a turbulent Mach 6 boundary layer has been determined from direct measurements of surface shear. Increasing the number of succeeding slots increases the skin-friction reduction, but this trend reverses at high injection rates. The incremental improvement in skin-friction reduction decreases with increasing number of slots. Comparison with previously reported step slot data indicates that step slots with tangential injection are more effective in reducing skin friction than the present flush slot configuration. Finite-difference predictions are in reasonable agreement with skin-friction and boundary-layer profile data.
Document ID
19760035885
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Srokowski, A. J. (NASA Langley Research Center Hampton, VA, United States)
Howard, F. G. (NASA Langley Research Center Hampton, VA, United States)
Feller, W. V. (NASA Langley Research Center High-Speed Aerodynamics Div., Hampton, Va., United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1976
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 76-178
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Washington, DC
Start Date: January 26, 1976
End Date: January 28, 1976
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
76A18851
Distribution Limits
Public
Copyright
Other

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