SPAN LOAD DISTRIBUTIONS RESULTING FROM CONSTANT VERTICAL ACCELERATION FOR THIN SWEPTBACK TAPERED WINGS WITH STREAMWISE TIPS SUPERSONIC LEADING AND TRAILING EDGES

摘要

On the basis of the linearized supersonic-flow theory, equations for the span load distribution resulting from constant vertical acceleration (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.nThe computational results of the investigation are presented in a 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.