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naca-tn-2445

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National Advisory Committee for Aeronautics, Technical Notes - Wind Tunnel Tests at Low Speed of Swept and Yawed Wings Having Various Plan Forms

Wind-tunnel tests of an exploratory nature have been made at low
speed of various small—scale models of sweptback, sweptforward, and
yawed wings. The tests covered changes in aspect ratio, taper ratio,
and tip shape. Some data were obtained with high-lift devices on
sweptback wings and with ailerons on sweptforward wings. The data have
been briefly analyzed and some comparisons have been made with the
available theory.

The results of the tests and the analyses indicated that the
values of lift-curve slope and effective dihedral of swept wings can?
be computed with a reasonable degree of accuracy in the low-lift-
coefficient range by means of existing theories.

In general, reducing the aspect ratio and the ratio of root chord
to tip chord resulted in increases in drag and effective dihedral and
increased the longitudinal stability near the stall. Cutting off the
tip of a sweptback wing normal to the leading edge reduced the effective
dihedral at low lift coefficients and gave a slight reduction in the
drag at high lift coefficients. Sweeping forward a part of the outer
panel of a sweptback wing improved the longitudinal stability and
decreased the effective dihedral but also slightly decreased the maximum
lift coefficient and increased the drag at high lift coefficients. The
use of high—lift devices at either the leading edge or the trailing edge
of sweptback wings increased the lift-drag ratio and the effective
dihedral at high lift coefficients. An increase in the ratio of root
chord to tip chord for sweptforward wings resulted in decreases in
aileron rolling-moment effectiveness that were greater than the values
computed for unswept wings.

Much interest in the use of highly swept wings has arisen since the
theory of reference 1 indicated the increases in flight critical Mach
number that could be obtained by the use of sweep. The effects of sweep
on the low-speed characteristics of wings have long been recognized and
theory (reference 2) indicates that the effects may be rather .large.
Some experimental data on untapered sweptback wings are provided in
reference 3. The present paper reports tests made on various swept and
yawed wings as an extension of the work of reference 3 to include the
additional effects of taper ratio and sweepforward and to provide data
for comparison with the theory of reference 2.

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naca-tn-2445

  • Version
  • 100 Downloads
  • 2.82 MB File Size
  • 1 File Count
  • December 15, 2016 Create Date
  • December 15, 2016 Last Updated
Scroll for Details

National Advisory Committee for Aeronautics, Technical Notes - Wind Tunnel Tests at Low Speed of Swept and Yawed Wings Having Various Plan Forms

Wind-tunnel tests of an exploratory nature have been made at low
speed of various small—scale models of sweptback, sweptforward, and
yawed wings. The tests covered changes in aspect ratio, taper ratio,
and tip shape. Some data were obtained with high-lift devices on
sweptback wings and with ailerons on sweptforward wings. The data have
been briefly analyzed and some comparisons have been made with the
available theory.

The results of the tests and the analyses indicated that the
values of lift-curve slope and effective dihedral of swept wings can?
be computed with a reasonable degree of accuracy in the low-lift-
coefficient range by means of existing theories.

In general, reducing the aspect ratio and the ratio of root chord
to tip chord resulted in increases in drag and effective dihedral and
increased the longitudinal stability near the stall. Cutting off the
tip of a sweptback wing normal to the leading edge reduced the effective
dihedral at low lift coefficients and gave a slight reduction in the
drag at high lift coefficients. Sweeping forward a part of the outer
panel of a sweptback wing improved the longitudinal stability and
decreased the effective dihedral but also slightly decreased the maximum
lift coefficient and increased the drag at high lift coefficients. The
use of high—lift devices at either the leading edge or the trailing edge
of sweptback wings increased the lift-drag ratio and the effective
dihedral at high lift coefficients. An increase in the ratio of root
chord to tip chord for sweptforward wings resulted in decreases in
aileron rolling-moment effectiveness that were greater than the values
computed for unswept wings.

Much interest in the use of highly swept wings has arisen since the
theory of reference 1 indicated the increases in flight critical Mach
number that could be obtained by the use of sweep. The effects of sweep
on the low-speed characteristics of wings have long been recognized and
theory (reference 2) indicates that the effects may be rather .large.
Some experimental data on untapered sweptback wings are provided in
reference 3. The present paper reports tests made on various swept and
yawed wings as an extension of the work of reference 3 to include the
additional effects of taper ratio and sweepforward and to provide data
for comparison with the theory of reference 2.

FileAction
naca-tn-2445 Wind Tunnel Tests at Low Speed of Swept and Yawed Wings Having Various Plan Forms.pdfDownload 
17,005 Documents in our Technical Library
2449514 Total Downloads

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Newest Additions

NASA-RP-1060 Subsonic Aircraft: Evolution and the Matching of Size to Performance
NASA-RP-1060 Subsonic Aircraft: Evolution and the Matching of Size to Performance
AA-CP-20212-001
AA-CP-20212-001
ADPO10769 Occurrence of Corrosion in Airframes
The purpose of this lecture is to provide an overview ...
MIL-STD-1759 Rivets and Rivet Type Fasteners Preferred for Design
The purpose of this book form standard is to provide ...
MIL-STD-810G Environmental Engineering Considerations and Laboratory Tests
This standard contains materiel acquisition program planning and engineering direction ...