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Contribution to the aerodynamics of rotating-wing aircraftThe chief defect of the investigations up to now was the assumption of a more or less arbitrary "mean" drag coefficient for a section of the blade. This defect is remedied through replacement of the constant coefficient by a function of higher order which corresponds to the polar curve of the employed profile. In that way it is possible to extend the theory to include the entire range from "autogyro" without power input to the driven "helicopter" with forward-tilted rotor axis. The treatment includes the twisted rectangular blade and a non-twisted tapered blade. Proceeding from the air flow and stresses on a section of the blade, the formulas for torque, axial and normal thrust of a linearly twisted rectangular blade, and a non-twisted tapered blade, are derived.
Document ID
19930094495
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Sissingh, G
Date Acquired
September 6, 2013
Publication Date
December 1, 1939
Report/Patent Number
NACA-TM-921
Accession Number
93R23415
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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