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National Advisory Committee for Aeronautics, Report - The Pressure Distribution Over the Horizontal Tail Surfaces of an Airplane, III

This report is the third 1 and final part of the investigation on the distribution of pressure
over the horizontal tail surfaces of an airplane, conducted by the National Advisory Committee
for Aeronautics at the Langley Memorial Aeronautical Laboratory. This part deals with the
distribution of pressure during accelerated flight of the full-sized airplane, for the purpose of
determining the magnitude of the tail and fuselage stresses in stunting.
As the pressures to be measured in accelerated flight change in value with great rapidity,
it was found that the liquid manometer used 1n the first part of this investigation would not be
at all suitable under these conditions; so it was necessary to design and construct a new manome-
ter containing a large number of recording diaphragm gauges for these measurements. Sixty
openings on the tail surfaces were connected to this manometer and continuous records of
pressures for each pair of holes were taken duringvarious maneuvers. There were also recorded,
simultaneously with the pressures, the normal acceleration at the center of gravity and the
angular position of all the controls.
The study of the tail load in accelerated flight has been considered of great importance,
first because there has been no experimental data of any kind upon which the designer could
base the strength of the fuselage and tail surfaces, and secondly because it has been believed
that the loads experienced by the tail surfaces and fuselage in accelerated flight would far exceed
those occuring under any other condition.