Lift and drag characteristics of a cabin monoplane Page: 3 of 22
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2 N.A.C.A. Technical Note No. 362
Measurements of the lift and drag characteristics of a
full scale cabi.n monoplane have been completed recently at the
Langley Memorial Aeronautical Laboratory of the National Ad-
visory. Committee for Aeronautics, Langley Field, Va. An air-
foil of the section used on the airplane has been tested recently
in the Variable Density Wind Tunnel, and it is possible to com-
pare the maximum lift coefficient obtained for the airfoil with
that obtained in flight for the complete airplane.
Lift, drag, and angle of attack were determined by direct
measurements of the gliding angle, dynamic pressure, and atti-
tude of the airplane in steady glides (Reference 1). The lift
and drag characteristics.were established for angles of attack
between -20 and +210 with the propeller locked in. a horizontal
position. The data obtained are tabulated,. and are also shown
by means of the usual polar diagram and curves of lift and drag
coefficients versus angle of attack.
In addition to tests with the propeller looked, glides at
angles of -attack of -10, 50, and 110 wete made With the propel-
ler operating. at approximately zero thrust. The reason for
making these, additional,tests was that, in connection with the
use of this latter method in previous tests, some doubt has
been expressed regarding the exactness with which the effect of
the propeller is eliminated by this method. An essential phase
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Thompson, F L & Keister, P H. Lift and drag characteristics of a cabin monoplane, report, January 1, 1931; (digital.library.unt.edu/ark:/67531/metadc54038/m1/3/: accessed October 18, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.