Conically cambered delta wings in supersonic flow. I - Basic solutions

摘要

The analysis of a conically cambered delta wing with subsonic leading edges in a supersonic stream is presented. The twist distribution chosen is a polynomial of even ordered terms in the conical coordinate for which a closed form series solution is obtained. It is found that the mean camber shapes are geometrically simple and appear to be promising in terms of low drag. To avoid flow separation at the leading edges at the design condition, the attachment line is prescribed which results in a leading edge droop for all basic shapes.