The applicability of sonic boom minimization concepts in the design of large supersonic transport airplanes capable of a 2500-nautical-mile range at a cruise Mach number of 2.7 is considered. Aerodynamics, weight and balance, and mission performance as well as sonic boom factors, have been taken into account. The results indicate that shock-strength nominal values of somewhat less than 48 newtons/sq m during cruise are within the realm of possibility. Because many of the design features are in direct contradiction to presently accepted design practices, further study of qualified airplane design teams is required to ascertain sonic boom shock strength levels actually attainable for practical supersonic transports. (Author)
Application of Sonic-Boom Minimization Concepts in Supersonic Transport Design
1973
59 pages
Report
Keine Angabe
Englisch
Design of Supersonic Biplane Aircraft Concerning Sonic Boom Minimization
British Library Conference Proceedings | 2010
|Sonic boom minimization schemes
AIAA | 1970
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