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
This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided to Digital Library by the UNT Libraries Government Documents Department.
The following text was automatically extracted from the image on this page using optical character recognition software:
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
Here’s what’s next.
This report can be searched. Note: Results may vary based on the legibility of text within the document.
Tools / Downloads
Get a copy of this page or view the extracted text.
Citing and Sharing
Basic information for referencing this web page. We also provide extended guidance on usage rights, references, copying or embedding.
Reference the current page of this Report.
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 February 22, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.