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Propfan Test Assessment (PTA)The objectives of the Propfan Test Assessment (PTA) Program were to validate in flight the structural integrity of large-scale propfan blades and to measure noise characteristics of the propfan in both near and far fields. All program objectives were met or exceeded, on schedule and under budget. A Gulfstream Aerospace Corporation GII aircraft was modified to provide a testbed for the 2.74m (9 ft) diameter Hamilton Standard SR-7 propfan which was driven by a 4475 kw (600 shp) turboshaft engine mounted on the left-hand wing of the aircraft. Flight research tests were performed for 20 combinations of speed and altitude within a flight envelope that extended to Mach numbers of 0.85 and altitudes of 12,192m (40,000 ft). Propfan blade stress, near-field noise on aircraft surfaces, and cabin noise were recorded. Primary variables were propfan power and tip speed, and the nacelle tilt angle. Extensive low altitude far-field noise tests were made to measure flyover and sideline noise and the lateral attenuation of noise. In coopertion with the FAA, tests were also made of flyover noise for the aircraft at 6100m (20,000 ft) and 10,668m (35,000 ft). A final series of tests were flown to evaluate an advanced cabin wall noise treatment that was produced under a separate program by NASA-Langley Research Center.
Document ID
Document Type
Contractor Report (CR)
Little, B. H. (Lockheed Aeronautical Systems Co. Marietta, GA, United States)
Poland, D. T. (Lockheed Aeronautical Systems Co. Marietta, GA, United States)
Bartel, H. W. (Lockheed Aeronautical Systems Co. Marietta, GA, United States)
Withers, C. C. (Lockheed Aeronautical Systems Co. Marietta, GA, United States)
Brown, P. C. (United Technologies Corp. Windsor Locks, CT., United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1989
Subject Category
Report/Patent Number
NAS 1.26:185138
Funding Number(s)
PROJECT: RTOP 535-03-01
Distribution Limits
Work of the US Gov. Public Use Permitted.

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NameType 19900002423.pdf STI