Lift and drag characteristics of a cabin monoplane determined in flight Page: 4 of 22

N.A.C.A. Technical Note No. 362

of this part of the program Was a determination of the drag of
the locked propeller and the propeller thrust characteristics
by means of tests with the complete airplane mounted in the Pro-
peller Research Tunnel. Although the results obtained with the
propeller rotating are strictly secondary in importance, they
are believed to be sufficiently important to warrant inclusion
herein.
Apparatus and Method
The airplane used for these tests (the Fairchild F-..2W2)
i's shown in Figures 1, 2, and 3. It is a closed-cabin high-
wing monoplane having a gross weight of approximately 4700 lb.
as flown in these tests. It has a Gottingen 38.7 wing section
with tips rounded and slightly tapered, as shovwh in Figures 2
and 3. The wing span is 50 feet; chord, 7 feet; area, 336
square feet; and aspect ratio (span), 7.4. The-area includes
area
the area between the wing roots that is assumed by the fuselage.
The angle of incidence of the wings is +2.6o with respect to the
thrust axis.
Propeller locked.- Dynamic pressure and gliding angle were
recorded with the N.A.C.A. flight-path-angle and air-speed re-
corder (Reference 2), which was suspended about 90 feet below
the airplane. The angle of the wing chord was recorded with an
N.A.C.A. recording pendulum inclinometer. The positions of the
three control surfaces were recorded with an N.A.C.A. control

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Thompson, F. L. & Keister, P. H. Lift and drag characteristics of a cabin monoplane determined in flight, report, January 1931; (digital.library.unt.edu/ark:/67531/metadc54038/m1/4/ocr/: accessed December 14, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.

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