Investigations on the Downwash Behind a Tapered Wing With Fuselage and Propeller Page: 27 of 52
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26 N.A.C.A. Technical Memorandum No. 876
This factor --- is constant if ] is a constant, for ex-
ample, for the"reference measurement" at which may be
put = 1.
Considering, on the contrary, polars with the param-
eters "cw = 0" and "full throttle" then
--- > 1 and equally dependent on a. The procedure in these
cases was to put ---= 1 and use a smaller angle of down-
wash aw* which in a way produces the actually greater re-
turning moment. The expression for aw* reads:
Cw* = aer -c HL -
w* = aer (aaer - aw + ) = ( - PB)
Now the stability criterion reads as
d M d aw*
--- = 1-
d a doa
It should be observed that the height level of the
tail is different at the different angles of attack. In
the following example, it is assumed at ch = +0.1 for
a = 00. Every angle of attack has a different ch fixed
in wind direction. figures 50 to 53, which show eq by
dot and dash can be used to establish the relation of
6 aw to A (and ca) (figs. 64 and 65) from which the re-
lated values of acw and a for body-fixed horizontal tail
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Muttray, H. Investigations on the Downwash Behind a Tapered Wing With Fuselage and Propeller, report, September 1938; (https://digital.library.unt.edu/ark:/67531/metadc63295/m1/27/: accessed April 25, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.