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RSRA sixth scale wind tunnel testThe sixth scale model of the Sikorsky/NASA/Army rotor systems research aircraft was tested in an 18-foot section of a large subsonic wind tunnel for the purpose of obtaining basic data in the areas of performance, stability, and body surface loads. The model was mounted in the tunnel on the struts arranged in tandem. Basic testing was limited to forward flight with angles of yaw from -20 to +20 degrees and angles of attack from -20 to +25 degrees. Tunnel test speeds were varied up to 172 knots (q = 96 psf). Test data were monitored through a high speed static data acquisition system, linked to a PDP-6 computer. This system provided immediate records of angle of attack, angle of yaw, six component force and moment data, and static and total pressure information. The wind tunnel model was constructed of aluminum structural members with aluminum, fiberglass, and wood skins. Tabulated force and moment data, flow visualization photographs, tabulated surface pressure data are presented for the basic helicopter and compound configurations. Limited discussions of the results of the test are included.
Document ID
19760013038
Document Type
Contractor Report (CR)
Authors
Flemming, R.
(Sikorsky Aircraft Stratford, CT, United States)
Ruddell, A.
(Sikorsky Aircraft Stratford, CT, United States)
Date Acquired
September 3, 2013
Publication Date
December 4, 1974
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
SER-72011
NASA-CR-144964
Accession Number
76N20126
Funding Number(s)
CONTRACT_GRANT: NAS1-13000
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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