• Version
• 134 Downloads
• 3.06 MB File Size
• 1 File Count
• January 17, 2017 Create Date
• January 17, 2017 Last Updated

National Advisory Committee for Aeronautics, Technical Notes - Span Load Distribution Resulting From Angle of Attack, Rolling, and Pitching for Tapered Sweptback Wings with Streamwise Tips - Supersonic Leading and Trailing Edges

On the basis of the linearized supersonic-flow theory the span load
distributions resulting from constant angle of attack, from steady rolling,
and from steady pitching were calculated for a series of thin sweptback
tapered wings with streamwise tips and- with swersonic leading and trailing
edges. The results are valid for the Mach number range for which the
Mach line from either wing tip does not intersect the remote half-wing.

The results of the analysis are presented as a series of design
charts. Some illustrative variations of the spanwise distribution of
circulation with the various design parameters are also presented.

A knowledge of aerodynamic spanwise loading is of yeat value in
performing aerodynamic calculations. In references 1 to 1L the linearized
upwash behind a lifting wing is shown to be largely determined by the
spanwise loading except for the region close to the trailing edge. It
may also be demonstrated that , except in the vicinity of the trailing
edge, the sidewash velocity component is also largely determined by the
spanwise loading. The aim of the present paper is to determine spanwise
loadings for a series of thin sweptback tapered wings with streamwise
tips and with supersonic leading and trailing edges. These spanwise
loadings can be utilized in connection with the estimation of flow fields
although the results of the analysis may also be applied to problems in
aerodynamic loads and aeroelasticity.

The spanwise distribution of circulation resulting from a constant
angle of attack was evaluated chiefly because of the significance of the
downwash induced by the wing on the horizontal tail surfaces. Similarly,
the spanwise distribution of circulation resulting from a constant rate
of roll was evaluated principally because of the Significance of the
velocities induced by the wing on the tail—surface contribution to
stability and damping. The spanwise distribution of circulation resulting
from a constant rate of pitch was evaluated because of the possible
importance of the downwash induced by the pitching wing on the horizontal
tail surfaces and because the downwash resulting from a pitching wing is
one component of the downwash induced by a wing with a constant vertical
acceleration. (See reference 5.)