Investigation at Supersonic Speeds of Some of the Factors Affecting the Flow Over a Rectangular Wing With Symmetrical Circular-Arc Section and 30-Percent-Chord Trailing-Edge Flap Page: 2 of 113
This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided to UNT Digital Library by the UNT Libraries Government Documents Department.
Extracted Text
The following text was automatically extracted from the image on this page using optical character recognition software:
n ASA TlhUNCLASSFIED
NACA RM LJ18 3 1176 01436 2496
NATIONAL ADVISORY CCMITTEE FOR AERONAUTICS
RESEARCH MEMORANDUM
INVESTIGATION AT SUPERSONIC SPEEDS OF SOME OF THE
FACTORS AFFECTING THE FLOW OVER A RECTANGULAR
WING WITH SYMMETRICAL CIRCULAR-ARC SECTION
AND 30-PERCENT-CHORD TRAILING-EDGE FLAP
By K. R. Czarnecki and James N. Mueller
SUMMARY
An investigation has been made at supersonic speeds of some of the
factors affecting the flow over a rectangular wing having a symmetrical
circular-arc section and a 30-percent-chord trailing-edge flap. Results
obtained over a Mach number range from 1.62 to 2.40 and at a Reynolds
number of 1.07 x 106 indicated that the laminar-flow separations and the
breaks or shifts in the section force and moment curves previously
encountered experimentally at M = 1.62 also occurred at the higher
test Mach numbers. When the boundary layer was made turbulent by fixing
transition, the flow separations were eliminated or reduced and the
agreement between the experimental and theoretical pressure distributions
and aerodynamic coefficients was generally greatly improved. A decrease
in the wing thickness from 9 percent to 6 percent not only improved the
drag and the lift-drag characteristics of the wing but also slightly
increased the flap effectiveness.
INTRODUCTION
As a result of the large number of airplanes and missiles being
designed for the supersonic speed range, a great need has arisen for
information on which to base the design of supersonic controls. In
order to meet this need, a number of theoretical and experimental inves-
tigations of the aerodynamic characteristics of controls at supersonic
speeds have been made (for example, references 1 through 12). Theo-
. retical flap characteristics alone are inadequate, however, because of
the existence of shock-boundary-layer interaction effects not considered
in the theory. Host of the experimental investigations so far reported,
on the other hand, have been limited to the transonic or low supersonic
UNCLASSIFIED
Upcoming Pages
Here’s what’s next.
Search Inside
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.
Czarnecki, K. R. & Mueller, James N. Investigation at Supersonic Speeds of Some of the Factors Affecting the Flow Over a Rectangular Wing With Symmetrical Circular-Arc Section and 30-Percent-Chord Trailing-Edge Flap, report, January 2, 1951; (https://digital.library.unt.edu/ark:/67531/metadc58826/m1/2/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.