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Advanced Supersonic Transport
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English
Abstract
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.
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Authors
Topic
Citation
FitzSimmons, R. and Roensch, R., "Advanced Supersonic Transport," SAE Technical Paper 750617, 1975, https://doi.org/10.4271/750617.Also In
References
- Magruder W. M. “The SST and the National Interest,” Department of Transportation Paper National Aeronautic Association November 11 1970
- “The SST A General Description,” Boeing D6A11850-1 April 1970
- FitzSimmons R. D. Hoover W. C. “AST - A Fifth Engine for Environmental Consideration,” SAE Paper 730899 October 1973
- FitzSimmons R. D. “NASA Advanced Supersonic Transport Program,” Testimony before the Subcommittee on Aeronautics and Space Technology, Committee on Science and Astronautics, House of Representatives 22 February 1974
- FitzSimmons R. D. Rowe W. T. “AST Propulsion Comparisons,” SAE Paper 750631 May 1975
- Howlett R. A. “Engine Design Considerations for Advanced Supersonic Transport Application,” SAE Paper 750628 May 1975
- Klus G. W. Welliver A. D. “Variable-Cycle Engines for the SST,” SAE Paper 750630 May 1975
- Radkey R. L. “An Analysis of the Impact of Cabin Floor Angle Restrictions on L/D for a Typical Supersonic Transport,” NASA CR-132508 August 1974