Investigations on the Downwash Behind a Tapered Wing With Fuselage and Propeller Page: 12 of 52
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N.A.C.A. Technical Memorandum No. 876
the course of the downwaeh on the vertical axis lying in
the~plane of symmetry (argument advanced by H. laulthopp).
These vortices near the plane of symmetry, moreover, lie,
as a result of the sinking of the vortex sheet with the
downwash, below the EZ axis and so produce the afore-
mentioned one-sided range of high downwash coefficients.
Further, it may be stated that the marginal portions
of the vortex sheet do not diminish in the same measure
as the inside portions. The marginal vortices rather lie -
as the earlier elliptical wing study (reforence 1) also in-
dicated - approximately at wing height. The maximum value
of the downwash component due to the marginal vortices
therefore lies about on the e axis (cf. reference 18).
The superposition of two assumedly separate theoreti-
cal downwash curves for marginal and inisde vortices gives
the actually unsymmetrical course of the curves, which, de-
pending upon the strength of the marginal and inside vor-
tices - affected by the lift distribution - is varyingly
According to the foregoing, a fairly good agreement
obtains between the theoretical and experimental values
when plotting a theoretical curve for a nonrolled-up vortex
sheet and than shifting it approximately by the amount of
the sinking of the vortex shoot.
Starting with a given lift distribution known from
reference 10, 11, or-12 we obtain with
a ----- and k = --
V + u ro
the following expression for the vertical axis in the plane
-- ( + )} - d.---
1 2+.- b~ eGa h) +a
~.t~" B C~B-~e
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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/m1/12/: accessed April 24, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.