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Theoretical Loading at Supersonic Speeds of Flat Swept-back Wings with Interacting Trailing and Leading Edges

Doris Cohen

出版	National Advisory Committee for Aeronautics, 1949
URL	http://books.google.com.hk/books?id=_7mfWqU1XWIC&hl=&source=gbs_api
EBook	FULL_PUBLIC_DOMAIN

註釋

By the method of superposition of conical flows, the load distribution is calculated for regions of a long swept-back wing behind the points at which the Mach lines from the trailing-edge apex intersect the leading edge. It is found that a good approximation on the load can be obtained by the application of a fairly simple correction factor to the two-dimensional subsonic distribution. The similarity of two-dimensional flow is used to derive expressions for the loss of lift behind the Mach lines from the tips of the wing.