Span load distribution resulting from constant vertical acceleration for thin sweptback

Isabella J. Cole, Kenneth Margolis
naca-tn-3120
Jan 1954


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.

An Adobe Acrobat (PDF) file of the entire report:
http://naca.central.cranfield.ac.uk/reports/1954/naca-tn-3120.pdf