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Pressure Distribution over the Rudder and Fin of an Airplane in FlightThis investigation was carried out by the National Advisory Committee for Aeronautics at the Langley Memorial Aeronautical Laboratory for the purpose of determining the loads which occur on the vertical tail surfaces in flight. The method consisted in measuring the pressures simultaneously at 28 points on the rudder and fin by means of a recording multiple manometer. The results show that the maximum load encountered in stunting was 7 pounds per square foot on the rudder and fin, and it is probable that this might rise to 10 pounds per square foot in a violent barrel roll; but in steady flight the average loads do not exceed 0.6 pound per square foot. The maximum load on the rudder and fin may occur at the same instant as the maximum load on the horizontal tail surfaces and the maximum normal acceleration. The torsional moment about the axis of the fuselage due to the rudder and fin may rise as high as 250 foot-pound. The results obtained from this investigation have a direct application to the design of the rudder, fin, and fuselage.
Document ID
19930091214
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Norton, F H
Brown, W G
Date Acquired
September 6, 2013
Publication Date
January 1, 1923
Report/Patent Number
NACA-TR-149
Accession Number
93R20504
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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