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An experimental investigation of propfan installations on an upswept supercritical wing at transonic Mach numbersAn investigation has been conducted in the Langley 16 Foot Transonic Tunnel to determine propfan installation and slipstream interference effects on an unswept supercritical wing. This data can be used for verification of existing and developing theoretical codes as well as giving an understanding of the flow interactions associated with propeller/nacelle/wing integration. The investigation was conducted over a Mach number range of 0.5 to 0.8 and at angles of attack from 0 deg to 3 deg. The propeller was powered by an air turbine simulator and the exhaust from the air turbine was used to simulate the exhaust from the propfan nacelle. Reynolds number based on wing chord varied from 3 to 4 million. Results indicate that the propfan causes an increase in the wing lift coefficient. It was found that most of the propeller induced swirl is recovered by the wing. The propeller slipstream also causes a large favorable leading edge suction peak on the upwash side and a smaller unfavorable decrease on the downwash side.
Document ID
19850022700
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Bartlett, G. R. (Vigyan Research Associates, Inc. Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
May 1, 1985
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-172605
NAS 1.26:172605
Accession Number
85N31013
Funding Number(s)
CONTRACT_GRANT: NAS1-17826
PROJECT: RTOP 505-43-90-07
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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