Wind tunnel pressure distribution tests on a series of biplane wing models Part III: effects of charges in various combinations of stagger, gap, sweepback, and decalage Page: 4 of 30
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N.A.C.A. Technical Note No. 330
2
back, stagger and decalage, and gap and decalage were investi-
gated. Two previous reports, Part I and Part II (See References),
covered the effects of variations of dihedral, overhang and each
of the above factors taken separately. A more complete presen-
tation of the results of the entire investigation and an analy-
sis from the standpoints of spinning, stalled flight, and struc-
tural design of biplane wings will be published at a later date.
The tests were made in the atmospheric wind tunnel of the
Langley Memorial Aeronautical Laboratory. A complete descrip-
tion of the models, apparatus, method of testing and procedure
in working up the test data is given in Part I (Reference 1)
and will not be rePeated here. The Clark Y profile was used on
each wing. Figure 1 shows the wing plan-form and location of
the pressure orifices.
Tests
The biplane arrangements tested were divided into four
groups as follows:
1. Variations in stagger and gap.
(Decalage = 0, dihedral = 0, sweepback = 0, over-
hang = .)
Gap/chord Stagger
a .75 - 0
b) .75 +25 per cent chord
c .75 +50 per cent chord
d 1.25 O
e 1.25 +25 per cent chord
f 1.25 +50 per cent chord
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Knight, Montgomery & Noyes, Richard W. Wind tunnel pressure distribution tests on a series of biplane wing models Part III: effects of charges in various combinations of stagger, gap, sweepback, and decalage, report, December 1929; (https://digital.library.unt.edu/ark:/67531/metadc54019/m1/4/: accessed April 18, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.