Lift and drag characteristics of a cabin monoplane determined in flight Page: 5 of 22
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N.A.C.A. Technical Note No. 362
position recorder (Reference 3).
Glides, with the propeller locked in a horizontal position,
were made at altitudes between 10,000 and 4,000 feet. Records
of 30 seconds. duration were obtained at various indicated air
speeds from the stalling speed of 60 m.p.h. to 140 m.p.h. The
glides were made with the horizontal stabilizer in one position
(angle of incidence with respect to thrust axis = +.90). Control
at and beyond maximum lift was obtained by installing a large fin
and rudder, shown in comparison with the standad surfaces in
Figure 4. Tests were made that established the fact that no
appreciable increase in drag accompanied the installation of
this additional tail structure. The drag of the suspended re-
cording instrument was established by direct measurements in
glides with the suspension cable attached to a spring balance
and angle indicator.
The lift and drag coefficients for the airplane were
found by use of the expressions
= W .cW.osY
and sis - d
where W is the total weight of the airplane during a glide,
Y. the recorded gliding angle,
q the recorded dynamic pressure,
S the total, wing area of 336 square feet,
and d the drag of the suspended instrument.
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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/m1/5/: accessed November 17, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.