Isabella J. Cole, Kenneth Margolis
tapered wings with streamwise tips 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.
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