Lift and drag characteristics of a cabin monoplane determined in flight Page: 6 of 22
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N.A.Q.A. Technical Note -No. 362
The ahgle of attack,. , is given by
where X is the recorded attitude angle of the wing measured
from the horizontal.
Pr6peler operat-ing at zero thrust.- Before any flight tests
were made, the drag of the propeller locked horizontally and a
portion of the thrust curve for the propeller were determined
with the complete airplane -mounted in the -Propeller Research
Tunnel. The propelled drag-was determined by the difference in
over-all drag with and without the propeller in place. The
thrust curve was established for values of V/nD near that for
zero thrust. The tunnel tests ere'emade with the thrust axis
parallel to the air stream; thus the angle of attack of the
wings was 2.6
The procedure followed in gliding was essentially the
same as that employed with the propeller locked except that
it was necessary to adjust the propeller speed to approxi-
mately the proper value for zero thrust for each gliding speed
and to obtain additional data from which the actual V/nD
attained could be calculated. The actual thrust developed in
flight was calculated from the known dynamic pressure, V/nD,
and thrust characteristics. It was added algebraically to the
apparent drag of the airplane calculated from the weight and
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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/m1/6/: accessed June 19, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.