Tank Tests of a 1/7-Size Dynamic Model of the Grumman XJR2F-1 Amphibian to Determine the Effect of Slotted- and Split-Type Flaps on Take-Off Stability - NACA Model 212, TED No. NACA 2378 Page: 3 of 22
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2 NACA RM No. LTAO7
deflections of the slotted flaps, the bow-down aerodynamic pitching
moments caused excessive lower-limit porpoising.
Additional tests of the model with the flap design changed
from the original slotted flap to a split flap of the same plan
form area was requested by the Bureau of Aeronautics in their
letter of March 27, 1946, Aer-RD-62-FWSL. It was requested that
the tests include the determination of the forward limits of the
center of gravity for stable take-offs with the stabilizer
incidence decreased and elevators at -300 in combination with the
split flap and slotted flap. It was thought that the reduction
in aerodynamic pitching moment with the split-type flap would be
great enough to permit stable take-offs with full down flaps at
forward positions of the center of gravity.
In accordance with the request of the Bureau of Aeronautics,
Navy Department, the forward limits for stable positions of the
center of gravity were determined with both types of flaps. These
data were obtained at two rates of forward acceleration. Sufficient
aerodynamic tests were made to determine the approximate lift and
pitching-moment characteristics with the two types of flaps.
DESCRIPTION OF THE MODEL
The principal dimensions and general arrangement of the model
are presented in reference 1. The stabilizer was set at -2 .50 to
the wing chord in accordance with changes that had been made in
the design of the full size . The angle of incidence of the stabilizer
is 20 less than that used during the tests described in reference l
The split flaps had the same plan form area as that of the
slotted flaps. The tip sections of the slotted and split flaps are
shown in figure 1.
APPARATUS AND PROCEDURE
The test procedure was similar to that used in reference 1.
Unless otherwise specified, the following conditions were
maintained for all of the tests:
Stabilizer, 2.5o to base line
Leading-edge slats on wing
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Land, Norman S. & Zeck, Howard. Tank Tests of a 1/7-Size Dynamic Model of the Grumman XJR2F-1 Amphibian to Determine the Effect of Slotted- and Split-Type Flaps on Take-Off Stability - NACA Model 212, TED No. NACA 2378, report, February 6, 1947; (digital.library.unt.edu/ark:/67531/metadc64241/m1/3/: accessed January 23, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.