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Ditching Tests of a 1/24-Scale Model of the Lockheed XR60-1 Airplane, TED No. NACA 235The ditching characteristics of the Lockheed XR60-1 airplane were determined by tests of a 1/24-scale dynamic model in calm water at the Langley tank no. 2 monorail. Various landing attitudes, flap settings, speeds, and conditions of damager were investigated. The ditching behavior was evaluated from recordings of decelerations, length of runs, and motions of the model. Scale-strength bottoms and simulated crumpled bottoms were used to reproduce probable damage to the fuselage. It was concluded that the airplane should be ditched at a landing attitude of about 5 deg with flaps full down. At this attitude, the maximum longitudinal deceleration should not exceed 2g and the landing run will be bout three fuselage lengths. Damage to the fuselage will not be excessive and will be greatest near the point of initial contact with the water.
Document ID
20050028618
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Fisher, Lloyd J. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Cederborg, Gibson A. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 22, 2013
Publication Date
January 1, 1948
Subject Category
Aircraft Stability And Control
Report/Patent Number
NACA-RM-SL8E17
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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