Span Load Distributions Resulting from Constant Angle of Attack, Steady Rolling Velocity, Steady Pitching Velocity, and Constant Vertical Acceleration for Tapered Sweptback Wings With Streamwise Tips Subsonic Leading Edges and Supersonic Trailing Edges
Abstract
On the basis of linearized supersonic-flow theory, the theoretical spanwise distributions of circulation (which are proportional to the span load distributions) resulting from constant angle of attack, steady rolling velocity, steady pitching velocity, and constant vertical acceleration were calculated for a series of thin, sweptback, tapered wings with streamwise tips. The analysis is valid at those speeds for which the wing is wholly contained between the Mach cones springing from the wing apex and the trailing edge of the root section, that is, subsonic leading edges and supersonic trailing edges. An added restriction is that the Mach cones emanating from the leading edges of the wing tips must not intersect on the wing. Formulas for the spanwise distributions of circulation are given in closed form. Numerical results are presented as a series of design charts from which the desired loading may be obtained for given values of aspect ratio, taper ratio, Mach number, and leading-edge sweepback. The axis of pitch is taken at the wing apex although, by use of the calculated results and a simple transformation, span load distributions for steady pitching velocity may be readily obtained for arbitrary location of the pitch axis. Variations of the spanwise distributions of circulation with the various plan-form parameters, Mach number, and axis-of-pitch location are also presented for illustrative purposes.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1952
- Accession Number
- ADA377050
Entities
People
- Kenneth Margolis
- Margery E. Hannah
Organizations
- National Aeronautics and Space Administration