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The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil: Suction coefficient analysisA swept supercritical wing incorporating laminar flow control at transonic flow conditions was designed and tested. The definition of an experimental suction coefficient and a derivation of the compressible and incompressible formulas for the computation of the coefficient from measurable quantities is presented. The suction flow coefficient in the highest velocity nozzles is shown to be overpredicted by as much as 12 percent through the use of an incompressible formula. However, the overprediction on the computed value of suction drag when some of the suction nozzles were operating in the compressible flow regime is evaluated and found to be at most 6 percent at design conditions.
Document ID
19910014785
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Brooks, Cuyler W., Jr. (NASA Langley Research Center Hampton, VA, United States)
Harris, Charles D. (NASA Langley Research Center Hampton, VA, United States)
Harvey, William D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:4267
L-16774
NASA-TM-4267
Accession Number
91N24098
Funding Number(s)
PROJECT: RTOP 505-61-21-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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