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Family of airfoil shapes for rotating bladesAn airfoil which has particular application to the blade or blades of rotor aircraft such as helicopters and aircraft propellers is described. The airfoil thickness distribution and camber are shaped to maintain a near zero pitching moment coefficient over a wide range of lift coefficients and provide a zero pitching moment coefficient at section Mach numbers near 0.80 and to increase the drag divergence Mach number resulting in superior aircraft performance.
Document ID
19840003068
Acquisition Source
Legacy CDMS
Document Type
Other - Patent
Authors
Noonan, K. W. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1983
Subject Category
Aerodynamics
Accession Number
84N11136
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-PATENT-4,412,664|NASA-CASE-LAR-12843-1
Patent Application
US-PATENT-APPL-SN-392096

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