The interference effects on an airfoil of a flat plate at mid-span position Page: 4 of 20
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N.A.C.A. Technical Note No. 403
thin :metal templets having 3/8-inch, 3/4-inch and 1-inch
radii, respectively. Figure 2 shows the airfoil-plate
combination with fillets ready for testing in the tunnel.
For the purpose of testing the airfoil alone, the
standard 3/16 by 5/8 inch sting was attached to th'e lower
sur-face of the model on the dummy section. This was
modified for a second test by replacing the standard
sting and dummy section with-a special sting constructed
of a quarter-inch steel rod attached to a steel plate
three-sixteenths inch thick conforming to the airfoil
profile. -This special stig eliminated the dissymmetry
of the model caused by the standard form and also offered
lower tare. The sting and the method of attachment of
the component parts is shown in Figure.
The interference plate was constructed from a se-
lected aluminum plate three-sixteenths inch thick. - The
general shape was that of a circular disk 18 inches in
diame.ter, modified-to accomodate a steel tail piece for
the 'angle-of-attack mechanidm and twio steel side pieces
for the purpose of supporting the plate horizontally
between the balance-support struts. The edges of the
plate were carefully streamlined and particular care was
taken to make the plate flat and to keep the surfaces
smooth. Holes' to receive the bolt and dowels were accu-
rately drilled to seciure proper alignment and were so
placed as to bring the leading .edge of the airfoil 5
inches from the nose of the plate.
The tests were made at an average Reynolds Number of
3,600,000 which was obtained by using an-air pressure in
the tunnel of approximately 20 atmospheres. This value
of the Reynolds Number corresponds approximately to the
value reached by a medium-sized airplane when flying
near minimum speed. The method of testing was essentially,
the same as that described in reference 2.
The airfoil and the: interference plate were each
tested under two different conditions of the model to
determine the accuracy and variation of the test data
with the .conditions. - The airfoil was first tested with
the standard sting and the tares were computed by appl'y-
ing an area factor t'o the tares determined for the 5 by
30 inch models. A second test was made of the airfoil.
with the pecial sting de'&sribed ab6ve aid' the tares were
determined by measuring .tbe: forces on the . pporting
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Ward, Kenneth E. The interference effects on an airfoil of a flat plate at mid-span position, report, December 1931; (https://digital.library.unt.edu/ark:/67531/metadc54039/m1/4/: accessed April 2, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.