Span load distributions resulting from angle of attack, rolling, and pitching for tapered sweptback wings with streamwise tips

John C. Martin, Isabella Jeffreys
naca-tn-2643
Jul 1952


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 supersonic 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.

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