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Flight investigation of the effect of tail configuration on stall, spin, and recovery characteristics of a low-wing general aviation research airplaneFlight tests were performed to investigate the stall, spin, and recovery characteristics of a low-wing, single-engine, light airplane with four interchangeable tail configurations. The four tail configurations were evaluated for effects of varying mass distribution, center-of-gravity position, and control inputs. The airplane tended to roll-off at the stall. Variations in tail configuration produced spins ranging from 40 deg to 60 deg angle of attack and turn rates of about 145 to 208 deg/sec. Some unrecoverable flat spins were encountered which required use of the airplane spin chute for recovery. For recoverable spins, antispin rudder followed by forward wheel with ailerons centered provided the quickest spin recovery. The moderate spin modes agreed very well with those predicted from spin-tunnel model tests, however, the flat spin was at a lower angle of attack and a slower rotation rate than indicated by the model tests.
Document ID
19870007382
Document Type
Technical Publication (TP)
Authors
Stough, H. Paul, III (NASA Langley Research Center Hampton, VA, United States)
Patton, James M., Jr. (NASA Langley Research Center Hampton, VA, United States)
Sliwa, Steven M. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
February 1, 1987
Subject Category
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number
NAS 1.60:2644
NASA-TP-2644
L-16194
Funding Number(s)
PROJECT: RTOP 505-61-41-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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