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naca-tn-2959

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Theoretical Investigation of the Suepersonic Lift and Drag of Thin, Sweptback Wings with Increased Sweep Near the Root

Formulas are derived by the use of linearized theory for the lift
and drag due to lift, at supersonic speeds, of thin, flat wings having
a discontinuity in the leading—edge sweep, the inboard portion of the
leading-edge being very highly swept and the outboard portion less so.
Examples are presented to show the effect of the bend in the leading
edge on the pressure distribution. The lift-curve slope and drag have
been calculated for several families of wings, all with straight trail—
ing edges. For two typical plan forms, the aerodynamic-center location
has been calculated through a limited range of supersonic Mach numbers.

The over—all characteristics of the wings studied show little
effect of the concentration of sweep near the root, in the absence of
thickness and viscosity, but appear to be determined primarily by the
sweep of the outer portion. However, there is a shift of the lifting
pressure away from the central portion of the wing and toward the lead—
ing edge of the outer portions. 'In most cases, there will also be a
region of high lift around the trailing edge of the root section. As
a result, the aerodynamic center is generally farther back than on com-
parable conventional wings. In the limited calculations made, no shift
of aerodynamic-center location with Mach number was observed. Similar
effects are to be expected on the wing of a wing-fuselage configuration
of similar plan form.

Considerable interest has been shown in the use of wing plan forms
incorporating a region of increased leading-edge sweep, similar to a
large fillet, near the wing root. The forward extension of the root
chord can provide both increased wing depth, with its structural
advantage, and a useful and accessible volume for the installation of
fixed equipment, fuel, air scoops, or complete power plants, depending
upon the airplane size and purpose. Such a wing plan form should be
particularly useful for an all-wing airplane because of the greater
flexibility allowed in the chordwise location of the major weight
items.

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naca-tn-2959

  • Version
  • 39 Downloads
  • 1.33 MB File Size
  • 1 File Count
  • January 20, 2017 Create Date
  • January 20, 2017 Last Updated
Scroll for Details

Theoretical Investigation of the Suepersonic Lift and Drag of Thin, Sweptback Wings with Increased Sweep Near the Root

Formulas are derived by the use of linearized theory for the lift
and drag due to lift, at supersonic speeds, of thin, flat wings having
a discontinuity in the leading—edge sweep, the inboard portion of the
leading-edge being very highly swept and the outboard portion less so.
Examples are presented to show the effect of the bend in the leading
edge on the pressure distribution. The lift-curve slope and drag have
been calculated for several families of wings, all with straight trail—
ing edges. For two typical plan forms, the aerodynamic-center location
has been calculated through a limited range of supersonic Mach numbers.

The over—all characteristics of the wings studied show little
effect of the concentration of sweep near the root, in the absence of
thickness and viscosity, but appear to be determined primarily by the
sweep of the outer portion. However, there is a shift of the lifting
pressure away from the central portion of the wing and toward the lead—
ing edge of the outer portions. 'In most cases, there will also be a
region of high lift around the trailing edge of the root section. As
a result, the aerodynamic center is generally farther back than on com-
parable conventional wings. In the limited calculations made, no shift
of aerodynamic-center location with Mach number was observed. Similar
effects are to be expected on the wing of a wing-fuselage configuration
of similar plan form.

Considerable interest has been shown in the use of wing plan forms
incorporating a region of increased leading-edge sweep, similar to a
large fillet, near the wing root. The forward extension of the root
chord can provide both increased wing depth, with its structural
advantage, and a useful and accessible volume for the installation of
fixed equipment, fuel, air scoops, or complete power plants, depending
upon the airplane size and purpose. Such a wing plan form should be
particularly useful for an all-wing airplane because of the greater
flexibility allowed in the chordwise location of the major weight
items.

FileAction
naca-tn-2959 Theoretical Investigation of the Suepersonic Lift and Drag of Thin, Sweptback Wings with Increased Sweep Near the Root.pdfDownload 
17,005 Documents in our Technical Library
2449933 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 ...