A Preliminary Study of Airplane Performance Page: 4 of 13
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- 3 -
c3?ntical at sea level. The total weight of the airplane and the
wing loading was approximately the same as before.
Airplane #3 had the Model E engine and the Eiffel 36 section
but the area was reduced by the use of two sets of lower wings
to 300 sq.ft. or 50 sq.ft. less than the standard airplane. The
king posts and overhang wires were also removed. The total weight
of this airplane was about 2200 lbs., making the wing loading 7. 3
lbs/sq9 ft.
Model #4 was a standard Navy Vought as shown in Figs. 3 and s.
4, All wires were etreamlinedand the engine was a Model E, The
total weight of the airplane ready to fly was 2050 lbs., giving
a wing loading of 7.2 lbs/sq.ft.
Method of Test.
All of the runs were made at a constant height by the aid of
a sensitive statoscope mounted on the pilot's instrument board.
The average altitude for all of these tests was approximately
2000 ft. and all the speeds have been corrected for density and
are therefore true speeds. The installation correction for the
airspeed head mounted on the wing was determined for each air-
plane by the following method: A streamlinebody with a pitot
tube in the nose and a stabilizing tail was lowered from the air-
plane by means of a steel wire ana two rubber tubes which connect-
ed the pitot and static opening to an airspeed dial on the ob-
server's instrument board. The airplane was then runrzthgought
the whole speed range and the difference between the readings of
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Norton, F. H. & Brown, W. G. A Preliminary Study of Airplane Performance, report, November 1922; (https://digital.library.unt.edu/ark:/67531/metadc53792/m1/4/: accessed April 23, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.