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Wind tunnel study of slot spoilers for direct lift controlAn investigation was conducted in a 300-mph 7- by 10- foot tunnel to obtain data for a slot spoiler direct lift control system. Slot spoilers are believed to have advantages over flap-type direct lift control (DLC) systems because of the small amount of power required for actuation. These tests, run at a Reynolds number of 1,400,000 showed that up to 78 percent of the lift due to flap deflection could be spoiled by opening several spanwise slots within the flaps. For a given lift change the drag change was significantly less than that which would be obtained by a variable flap DLC system. A nozzle-shaped slot was the most effective of the slot shapes tested.
Document ID
19720006329
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Andrisani, D., II
(NASA Langley Research Center Hampton, VA, United States)
Gentry, G. L., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Stickle, J. W.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
January 1, 1972
Subject Category
Aerodynamics
Report/Patent Number
NASA-TN-D-6627
L-8014
Report Number: NASA-TN-D-6627
Report Number: L-8014
Accession Number
72N13978
Funding Number(s)
PROJECT: RTOP 760-71-03-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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