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Application of sonic-boom minimization concepts in supersonic transport designThe 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.
Document ID
19730015338
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Carlson, H. W. (NASA Langley Research Center Hampton, VA, United States)
Barger, R. L. (NASA Langley Research Center Hampton, VA, United States)
Mack, R. J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
June 1, 1973
Subject Category
Aircraft
Report/Patent Number
NASA-TN-D-7218
L-8767
Accession Number
73N24065
Funding Number(s)
PROJECT: RTOP 501-06-11-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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