Lift and drag characteristics of a cabin monoplane Page: 2 of 22
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q NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
TEC-NIOAL NOTE NO. 362
LIFT AND DRAG CHARACTERISTICS OF A CABIN MONOPLANE
DETERMINED IN FLIGHT
By F. L. Thompson and P. H. Keister
The results of flight.tests-conducted by the National
Advisory Committee for. Aeronautics to -determine the lift and
drag charbteristics of i full-sdale airplane are given herein.
A Faiedhild F70-.W2 cabin monoplane- having a GSttingen. 387 wing
section'Was used for the-tests.
Tlhe: maximum lift coefficientfor- the airplane is'compared
with th-at obtained for the GStt.ingen387 airfoil in recent tests
in the Variable Density Tunnel. The maximum lift coefficient
for the airplane was found to be 1.50 and that for the airfoil
1.56. Although the flight tests' were confined chiefly to glides
with the propeller locked horizontally, data obtained with the
propeller operating at zero thrust for a "few angles of attack
are also included. The 'most important feature of a comparison
between the results obtained with the propeller locked and
propeller rotating is that the"-difference in overall drag agrees
very well with that found' for the'-loked propeller in tests with
the airplane mounted in the Propeller Research Tunnel.
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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/m1/2/: accessed March 18, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.