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naca-tn-3120

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National Advisory Committee for Aeronautics, Technical Notes - Span Load Distributions Resulting from Constant Vertical Acceleration for Thin Sweptback Tapered Wings with Streamwise Tips - Supersonic Leading and Trailing Edges

On the basis of the linearized supersonic-flow theory, equations
for the Span load distribution resulting from constant vertical accel—
eration (that is, linear variation of angle of attack with time) are
derived for a series of thin sweptback tapered wings with streamwise
tips. The analysis is valid at Mach numbers for which the wing leading
and trailing edges are supersonic. A minor restriction is that the Mach
line from the leading edge of either wing tip may not intersect the
remote half wing.

The computational results of the investigation are presented in a
q series of charts from which the span loadings may be obtained for given
values of aspect ratio, taper ratio, leading-edge sweepback, and Mach
number. For illustrative purposes, variations of the spanwise distri-
bution of circulation (which is proportional to the span load distribu-
tion) with several plan-form parameters and Mach number are shown, in
addition to some typical chordwise and spanwise pressure distributions.

The aerodynamicist requires detailed information on the load dis-
tribution over the component surfaces of an airframe. One of the most
important considerations is the distribution of load along the wing
span. This information can be used directly to obtain the forces. and
moments acting on the wing itself and to estimate roughly the load on
isolated vertical tails (for corresponding motions) and isolated hori-
zontal tails; in addition, knowledge of the Span load distribution is
a prime requirement for the solution of problems relating to loads and
aeroelasticity and for flow-field and other aerodynamic calculations.
Thus, much effort has been devoted to developing methods of calculation
and utilizing these methods to obtain detailed load information through-
out the range of flight speeds for wings of various plan forms undergoing
several types of motion.

Some of the more recent contributions to the literature on Span
load distributions at supersonic speeds are references 1 to h. The
general plan form considered in these references has arbitrary aspect
ratio, taper ratio, and sweepback; the wing tips are parallel to the
axis of wing symmetry. At Mach numbers for which the wing leading edge
is subsonic, equations and charts for the Span load distributions
resulting from constant angle of attack, steady rolling, steady pitching,
and constant vertical acceleration are given in reference 1; the case of
constant sideslip is treated in reference 2.

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naca-tn-3120

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

National Advisory Committee for Aeronautics, Technical Notes - Span Load Distributions Resulting from Constant Vertical Acceleration for Thin Sweptback Tapered Wings with Streamwise Tips - Supersonic Leading and Trailing Edges

On the basis of the linearized supersonic-flow theory, equations
for the Span load distribution resulting from constant vertical accel—
eration (that is, linear variation of angle of attack with time) are
derived for a series of thin sweptback tapered wings with streamwise
tips. The analysis is valid at Mach numbers for which the wing leading
and trailing edges are supersonic. A minor restriction is that the Mach
line from the leading edge of either wing tip may not intersect the
remote half wing.

The computational results of the investigation are presented in a
q series of charts from which the span loadings may be obtained for given
values of aspect ratio, taper ratio, leading-edge sweepback, and Mach
number. For illustrative purposes, variations of the spanwise distri-
bution of circulation (which is proportional to the span load distribu-
tion) with several plan-form parameters and Mach number are shown, in
addition to some typical chordwise and spanwise pressure distributions.

The aerodynamicist requires detailed information on the load dis-
tribution over the component surfaces of an airframe. One of the most
important considerations is the distribution of load along the wing
span. This information can be used directly to obtain the forces. and
moments acting on the wing itself and to estimate roughly the load on
isolated vertical tails (for corresponding motions) and isolated hori-
zontal tails; in addition, knowledge of the Span load distribution is
a prime requirement for the solution of problems relating to loads and
aeroelasticity and for flow-field and other aerodynamic calculations.
Thus, much effort has been devoted to developing methods of calculation
and utilizing these methods to obtain detailed load information through-
out the range of flight speeds for wings of various plan forms undergoing
several types of motion.

Some of the more recent contributions to the literature on Span
load distributions at supersonic speeds are references 1 to h. The
general plan form considered in these references has arbitrary aspect
ratio, taper ratio, and sweepback; the wing tips are parallel to the
axis of wing symmetry. At Mach numbers for which the wing leading edge
is subsonic, equations and charts for the Span load distributions
resulting from constant angle of attack, steady rolling, steady pitching,
and constant vertical acceleration are given in reference 1; the case of
constant sideslip is treated in reference 2.

FileAction
naca-tn-3120 Span Load Distributions Resulting from Constant Vertical Acceleration for Thin Sweptback Tapered Wings with.pdfDownload 
17,005 Documents in our Technical Library
2449673 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 ...