Technical Aspects of the 1934 International Touring Competition (Rundflug) Page: 15 of 34
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1T.A.C.A. Technical Memorandum No. 760
But lack.. of time for exhaustive trials before the race
finally caused the designers to add a very small nor-
mal aileron directly at the wing tip and to connect it
with the interceptor (fig. 15b). This combination has
proved quite effective. Still it presents only a tempo-
rary solution. The final design is held in abeyance un-
til after the raco
Fie.seler Fi 97.- This airplane presents some new de-
partures in aerodynamic design. The wing is fitted with
Handley Page-Lachmann auto slots, extending over about
0.55 m (1.80 ft.) of the semispan. The original inten-
tion was to have only a wing-tip slot of 0.4 over the
semispan, but this was found to be insufficient for main-
taining adequate lateral stability (strongly trapezoidal
wing contour). Lack of time then resulted in the fitting
of a temporary inner portion (slotted wing without spe-
cial form). However, the tip of the slotted wing is un-
like that which English tests had shown to be favorable.
In addition, the airplane was fitted. with a Fowler-
type auxiliary wing, which rolls out and down and at the
same time increases the wing area (Q 2.8 m (9.19 ft.) = N
18 percent) in chord direction (figs. 16 and 17). It also
forms a slot between the normal wing trailing edge and the
auxiliary wing. U. S. wind-tunnel tests on the Fowler
wing manifested very high maximum lift coefficients which,
referred to the original wing area, amount to about 3.15
and together with slotted wing, to about 3.60. It was
also found that the ca ax for the wing with extended and
retracted auxiliary wing lies at approximately the same
angle of attack, which likewise is propitious for the
landing conditions. Admittedly, there is a very abrupt
drop in lift after reaching cma. or that reason the
addition of wing-tip slots with the object of maintaining
adequate lateral stability in stalling appears particular-
As the flap continues along the span a special type
of aileron, similar to a split flap, was used rather than
the conventional aileron. The ailerons deflect only up-
ward (fig. 18) and, specifically, only at the side of the
wing where a down motion of the wing is to be initiated.
With flap retracted the aileron acts almost exclusively as
split flap, although with lateral control movement a back-
ward aileron movement is also initiated because of the fact
that its center of rotation lies far above it. Contrari-
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Schulz, R. & Pleines, W. Technical Aspects of the 1934 International Touring Competition (Rundflug), report, December 1934; (https://digital.library.unt.edu/ark:/67531/metadc63467/m1/15/: accessed May 22, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.