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Estimation of the Spin and Recovery Characteristics of the North American XSN2J-1 AirplaneThe probable spin and recovery characteristics of the XSN2J-1 air-plane have been estimated on the basis of the results of brief test a performed on a model of an airplane of somewhat similar design. The spin-recovery tail-parachute requirements for the airplane were also determined end, in addition, an analysis was made to determine the best method of emergency pilot escape during a spin. The results of the investigation indicate that the recovery characteristics of the airplane will be satisfactory for all probable loading conditions of the airplane. A 6-foot-diameter tall parachute attached to a 30-foot tow-line will be satisfactory as a spin-recovery device for emergency recovery from demonstration spins. If the occupants of the airplane decide to abandon the airplane in a spin, they should leave the airplane from the outboard side of the cockpit and as far rearward as possible.
Document ID
20050019393
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Snyder, Thomas L. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 22, 2013
Publication Date
June 23, 1947
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NACA-RM-L7F23b
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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