NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Design and analytical study of a rotor airfoilAn airfoil section for use on helicopter rotor blades was defined and analyzed by means of potential flow/boundary layer interaction and viscous transonic flow methods to meet as closely as possible a set of advanced airfoil design objectives. The design efforts showed that the first priority objectives, including selected low speed pitching moment, maximum lift and drag divergence requirements can be met, though marginally. The maximum lift requirement at M = 0.5 and most of the profile drag objectives cannot be met without some compromise of at least one of the higher order priorities.
Document ID
19800017768
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Dadone, L. U. (Boeing Vertol Co. Philadelphia, PA, United States)
Date Acquired
September 4, 2013
Publication Date
May 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-2988
D210-11239-1
Accession Number
80N26267
Funding Number(s)
CONTRACT_GRANT: NAS1-14659
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available