Aerodynamic characteristics of two 25-percent-area trailing-edge flaps on an aspect ratio 2 triangular wing at subsonic and supersonic speeds Page: 2 of 83
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TECH LIBRARY KAFB, NM
1D NACA RM A52DOlcS 0 14289?
NATIONAL ADVISORY CMITN]T E FOR AERONAUTICS
AERODYNAMIC CHARACTERISTICS OF TWO 25-PERCENT--AREA
TRAILING-EDGE FLAPS ON AN ASPECT RATIO 2
TRIANGULAR WING AT SUBSONIC AND
By John W. Boyd.
The results of an experimental investigation of flap-type controls
on a low-aspect-ratio triangular wing using NACA 0005-63 sections are
presented for a constant-chord. and a constant-percent-chord control
surface. Two flap profiles were investigated, one having a true contour
and the other a blunt trailing edge. The lift, drag, pitching moment,
hinge moment, and rolling moments were obtained for Mach numbers of 0.6,
0.8, 0.9, 1.3, 1.53, and 1.7 at a constant Reynolds number of 3.0 million
and for angles of attack from -4O to 160. The flap deflections were
varied in 50 increments from +50 to -250.
The results showed that the flap plan form had little effect on the
lift effectiveness. The effects of flap plan form were more pronounced
on the pitching-moment effectiveness, the constant-chord flap exhibiting
the higher pitching-moment effectiveness throughout the speed ranges
investigated. Both flaps showed a considerable reduction in effective-
ness as the Mach number was increasec from 0.9 to 1.3. The constant-
percent-chord flap showed considerably lower values of the hinge-moment
parameters than did the constant-chord flap for the ranges of Mach
numbers investigated. For the constant-chord flap, thickening the flap
profile resulted in somewhat higher absolute values of the hinge-moment
parameter Ch throughout the Mach number range. For the constant-
percent-chord flap, thickening the flap profile resulted in considerably
higher absolute values of 0h in the subsonic speed range with little
effect being evident in the supersonic speed range. A comparison of the
measured values of the effectiveness and binge-moment parameters in the
supersonic speed range with the theory showed that the linearized theory
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Boyd, John W. Aerodynamic characteristics of two 25-percent-area trailing-edge flaps on an aspect ratio 2 triangular wing at subsonic and supersonic speeds, report, July 22, 1952; (digital.library.unt.edu/ark:/67531/metadc59373/m1/2/: accessed September 24, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.