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Wind tunnel investigation of an upper surface blown jet-flap powered-lift configurationAn investigation has been conducted in the Langley full-scale tunnel to determine the performance and static stability and control characteristics of a four-engine, upper surface blown jet-flap powered-lift configuration with a swept wing. The investigation included test performed over a range of angle of attack (-4 deg to 36 deg), angle of sideslip (-5 deg to 5 deg), and thrust coefficients (0 to 4.32) for both symmetric and engine-out power conditions and for horizontal and vertical tails both on and off. In addition to the four-engine tests, a few tests were made with the outboard engines removed to simulate a twin-engine powered-lift transport configuration.
Document ID
19740003719
Document Type
Other - NASA Technical Note (TN)
Authors
Phelps, A. E., III (Army Air Mobility R and D Lab. Hampton, Va., United States)
Smith, C. C., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1973
Subject Category
AIRCRAFT
Report/Patent Number
L-9051
NASA-TN-D-7399
Funding Number(s)
PROJECT: RTOP 760-61-02-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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NameType 19740003719.pdf STI