Advanced Supersonic Transport

Comparisons are presented between the last U.S. SST design and results of recent progress on an advanced supersonic transport design. The results are shown of changing from a double-delta 2.7 Mach configuration to a modified arrow-wing 2.2 Mach design. Information is presented covering increased range, lower operating cost, reduced technical risk, and noise levels that meet anticipated requirements of society.

The main emphasis in this paper is on an aerodynamic lift-to-drag ratio of 10 and how this high level of aerodynamic cruise efficiency can be substantiated for a tailored design.