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Investigation to Determine the Effectiveness of a Split-Aileron Type Emergency Spin-Recovery Device for the Northrop XF-89 AirplaneThe present paper presents the results of a brief investigation made to determine the effectiveness of a proposed emergency spin-recovery device to be used during demonstration spins of the Northrop XF -89 airplane. The proposed device makes use of split-type ailerons deflected +/-60deg on the outboard wing (left wing in a right spin). Tests made on a model which represented the airplane to a scale of 7 indicated that, if an uncontrollable spin is obtained in the design gross--weight loading, the device is not sufficiently effective to insure recovery,
Document ID
20090023711
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Neihouse, A. I. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Lee, H. A. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 24, 2013
Publication Date
August 31, 1951
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NACA-RM-SL-51H24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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