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National Advisory Committee for Aeronautics, Report - Wind Tunnel Tests on a Series of Wing Models Through a Large Angle of Attack Range Part I - Force Tests

This investigation coeersjorce tests through a large range of angle of attack on a series of mono-
plane and biplane wing models. The tests were conducted in. the atmospheric wind tunnel of the
National Advisory Committee for Aeronautics. The models were arranged in such a manner as to
make possible a determination of the ejects of variations in tip shape, aspect ratio, flap setting,
stagger, gap, decalage, sweep hack, and aizfofl profile. The arrangements represented most of the
types of wing systems in use on. modern airplanes.
The eject of each variable is illustrated by means of groups of curres. In addition, there are
included appromimate airtorotational characteristics in the form. of calculated ranges of “rotary
instability.
A correction for blocking in this tunnel which applies to monoplanes at large angles of attack
has been developed, and is gieen in an appendix.
The need of greater safety In airplane flight leads to a consideration of the characteristics
of wing systems at low speeds or large angles of attack. In general, the region of danger lies
above the angle of mammurn lift, and comparatively little information has been published relating
to the landing, spinning, stability, and controllability of airplanes 1n this region.
In order to augment the information on this subject, a comprehensive test program is
being carried out In the atmospheric wind tunnel at the Langley Memorial Aeronautical Labor-
atory. This program includes force, pressure distribution, and autorotation tests on a series of
models representing most of the Wing systems in use on modern airplanes. The angle of
attack range of the tests is sufficiently large to cover practically all attitudes attainable by an
airplane in flight.