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Wind tunnel tests of a full-scale model of a light twin-engine airplane with fixed auxiliary airfoil or leading-edge slotAn investigation has been conducted by means of wind-tunnel tests of a full-scale mockup of a light twin-engine airplane configuration to determine the effects of outboard partial-span slots and of auxiliary airfoils ahead of the leading edge of the wing in improving aerodynamic characteristics at high angles of attack. Both of the stall-control devices gave considerable improvement in high angle-of-attack characteristics with the auxiliary airfoil giving the more favorable results, but neither device performed as well as might have been expected.
Document ID
19740011552
Document Type
Other - NASA Technical Note (TN)
Authors
Fink, M. P. (NASA Langley Research Center Hampton, VA, United States)
Shivers, J. P. (NASA Langley Research Center Hampton, VA, United States)
White, L. C. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
April 1, 1974
Subject Category
AIRCRAFT
Report/Patent Number
NASA-TN-D-7474
L-9225
Funding Number(s)
PROJECT: RTOP 760-60-01-16
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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