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Investigation of the Kline-Fogleman airfoil section for rotor blade applicationsWind tunnel tests of a wedgeshaped airfoil with sharp leading edge and a spanwise step were conducted. The airfoil was tested with variations of the following parameters: (1) Reynolds number, (2) step location, (3) step shape, (4) apex angle, and (5) with the step on either the upper or lower surface. The results are compared with a flat plate and with wedge airfoils without a step having the same aspect ratio. Water table tests were conducted for flow visualization and it was determined that the flow separates from the upper surface at low angles of attack. The wind tunnel tests show that the lift/drag ratio of the airfoil is lower than for a flat plate and the pressure data show that the airfoil derives its lift in the same manner as a flat plate.
Document ID
19750006642
Document Type
Contractor Report (CR)
Authors
Lumsdaine, E. (Tennessee Univ. Knoxville, TN, United States)
Johnson, W. S. (Tennessee Univ. Knoxville, TN, United States)
Fletcher, L. M. (Tennessee Univ. Knoxville, TN, United States)
Peach, J. E. (Tennessee Univ. Knoxville, TN, United States)
Date Acquired
September 3, 2013
Publication Date
December 15, 1974
Subject Category
AERODYNAMICS
Report/Patent Number
NASA-CR-141282
AE-74-1054-1
Funding Number(s)
CONTRACT_GRANT: NSG-1054
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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