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• August 26, 2016 Create Date
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National Advisory Committee for Aeronautics, Report - Static Thrust of Airplane Propellers

The static thrust of a propeller was formerly of
interest only in connection with proposed helicopter
designs, but the advent of very high powers and
corresponding high performance in recent airplane
designs have made in necessary to consider the static
thrust as a design factor. At present the chief appli-
cations of accurate static thrust data are in the calcu-
lation of nosing-over moments and the estimation of
take-off runs.
The available methods of calculating static thrust
are based on constants derived from Durand and
Lesley’s tests on wooden propellers. (Reference 4.)
It is the purpose of this report to revise the constants
and to extend the methods to include recent data on
adjustable metal propellers.
In Chapter XIV of reference 2, Mr. Warner states:
“It can be shown from propeller theory that the
static thrust per horsepower for a propeller is equal to
a constant divided by the product of the r. p. m. of
the propeller and its diameter, and experiments by
Durand have shown that the average value of the
constant ranges from 49,000 for propellers'designed to
work normally at a value of V/nD of 1.1 up to 79,000
when V/nD for maximum efficiency is 0.5 - - — ~.
The variation of the coefficient is approximately
linear between the points given.”